Generalized jet-effect and enhanced devices

Abstract

The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter providing generalized equations of fluid motion and is generalized and translated into terms of electromagnetism. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable generalized fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.

Claims

1. An adapted convergent-divergent tunnel comprising two open butt-ends: inlet and outlet, and having a spatially varying cross-sectional area A(x) dependent on an x-coordinate along an x-axis being aligned with said adapted convergent-divergent tunnel's length; the spatially varying cross-sectional area A(x) defining a tunnel geometry having: (a) a convergent funnel having said an open inlet butt-end, (b) a narrow throat having a shape comprising: a narrowing sub-stage, a cross-section of minimal cross-sectional area, indicated by A.sub.*, said cross-section is located at a certain said x-coordinate called a critical condition point, indicated by x.sub.*, and a divergent sub-stage, and (c) a divergent exhaust tailpipe having said open outlet butt-end; said adapted convergent-divergent tunnel is exposed to a flowing fluid of at least one of liquid, gas, electrolyte, electron gas, and plasma, such that an incoming portion of said flowing fluid: enters said open inlet butt-end with an incoming velocity-vector, becomes a flowing fluid inward portion filling said spatially varying cross-sectional area A(x) of the adapted convergent-divergent tunnel completely, thereby, resulting in that said adapted convergent-divergent tunnel's spatially varying cross-sectional area A(x) being identical with said flowing fluid inward portion's varying cross-sectional area, thereby providing for said flowing fluid inward portion becoming a convergent-divergent; flows along said adapted convergent-divergent tunnel with a varying velocity-vector characterized by a value called M-velocity and denoted M(x) measured relative to said adapted convergent-divergent tunnel in Mach numbers, and exits through said open outlet butt-end with an outflowing velocity-vector; wherein an inner surface of said adapted convergent-divergent tunnel comprising surface portions being at least one of repellent, inert, and sticking with respect to said flowing fluid; wherein the tunnel geometry is adapted to an M-velocity of the incoming portion of said flowing fluid to allow for the flowing fluid inward portion to reach a specific M-velocity, indicated by M.sub.*, at the critical condition point x.sub.*, where M.sub.*=√{square root over ((γ−1)/γ)} and γ is adiabatic compressibility parameter of said flowing fluid; and wherein, as the tunnel geometry and distribution of the flowing fluid flowing fluid M-velocity, static pressure, absolute temperature, and density along said adapted convergent-divergent tunnel being mutually-predetermined according to the equation of continuity and the Bernoulli theorem, the tunnel geometry is further adapted to produce gradual distributions of the M-velocity, static pressure, absolute temperature, and density respectively in an adiabatic process by the spatially varying cross-sectional area A(x) satisfying an equation of M-velocity derived from the equation of continuity for an adiabatic process as follows: $A (x) = \frac{A_{*}}{M (x)} {(\frac{γ - 1}{γ})}^{\frac{1}{2}} {(\frac{2 + {γ (M (x))}^{2}}{γ + 1})}^{\frac{y + 1}{2 (γ - 1)}},$ where M(x) is a monotonic smooth function selected from at least one of: M.sub.M(x)=M(x), where: M(x) is a specific linear distribution of said flowing fluid M-velocity along the x-axis: M(x)=M.sub.*+α.sub.M(x−x.sub.*), and α.sub.M=∂M(x)/∂x is a constant gradient of the M-velocity specific linear distribution along the x-axis within the adapted convergent-divergent tunnel, when it is preferred a linear change of the M-velocity of a flowing fluid inward portion as the flowing fluid inward portion moves through the adapted convergent-divergent tunnel; $M_{\bar{P}} (x) = \sqrt{2 {{[P_{0} / \bar{P} (x)]}^{(γ - 1) / γ} - 1} / γ,}$ where: P.sub.0 is the stagnation pressure, P(x) is a specific linear distribution of said flowing fluid static pressure specified as: P(x)=P.sub.*+α.sub.P(x−x.sub.*), P.sub.* is the static pressure of said flowing fluid inward portion at the critical condition point x.sub.*, and α.sub.P=∂P(x)/∂x is a constant gradient of the static pressure specific linear distribution along the x-axis within the adapted convergent-divergent tunnel, when it is preferred a linear change of the flowing fluid inward portion static pressure as the flowing fluid inward portion moves through the adapted convergent-divergent tunnel; $M_{\bar{T}} (x) = \sqrt{2 {[T_{0} / \bar{T} (x)] - 1} / γ},$ where: T.sub.0 is the stagnation temperature, T(x) is a specific linear distribution of said flowing fluid temperature specified as: T(x)=T.sub.*+α.sub.T(x−x.sub.*), T.sub.* is the temperature of said flowing fluid inward portion at the critical condition point x.sub.*, and α.sub.T=∂T(x)/∂x is a constant gradient of the temperature specific linear distribution along the x-axis within the adapted convergent-divergent tunnel, when it is preferred a linear change of said flowing fluid inward portion temperature as the flowing fluid inward portion moves through the adapted convergent-divergent tunnel; and $M_{\overline{ρ}} (x) = \sqrt{2 {{[ρ_{0} / \overline{ρ} (x)]}^{(γ - 1)} - 1} / γ},$ where: ρ.sub.0 is the stagnation density, ρ(x) is a specific linear distribution of said flowing fluid density specified as: ρ(x)=ρ.sub.*+α.sub.ρ(x−x.sub.*), ρ.sub.* is the density of said flowing fluid inward portion at the critical condition point x.sub.*, and α.sub.ρ=∂ρ(x)/∂x is a constant gradient of the density specific linear distribution along the x-axis within the adapted convergent-divergent tunnel, when it is preferred a linear change of the flowing fluid inward portion density as the flowing fluid inward portion moves through the adapted convergent-divergent tunnel; thereby providing that the tunnel geometry is adapted to: correspond to the flowing fluid M-velocity such that variation of the M-velocity, static pressure, absolute temperature, and density remain substantially gradual as said flowing fluid moves within and along the adapted convergent-divergent tunnel, prevent jumps of the flowing fluid M-velocity, static pressure, absolute temperature, and density within said adapted convergent-divergent tunnel, prevent generation of unwanted waves in said flowing fluid, and provide for said flowing fluid laminar motion through said adapted convergent-divergent tunnel.

2. A specifically shaped tunnel being a portion of the adapted convergent-divergent tunnel of claim 1; wherein: a principal interval of the x-coordinates is defined as a fragment of the x-axis comprising at least the x-coordinates corresponding to a location of the adapted convergent-divergent tunnel between said open inlet butt-end and said open outlet butt-end; a Venturi M-velocity is defined as said M-velocity, lower than the specific M-velocity M.sub.* and low sufficient to cross trough said specifically shaped tunnel with said M-velocity remaining lower than the specific M-velocity M.sub.*, a de Laval low M-velocity is defined as said M-velocity, lower than the specific M-velocity M.sub.* and high sufficient to reach the specific M-velocity M.sub.* at said critical condition point x.sub.* belonging to the principal interval of the x-coordinates, a de Laval high M-velocity is defined as said M-velocity, higher than the specific M-velocity M.sub.* and low sufficient to reach the specific M-velocity M.sub.* at said critical condition point x.sub.* belonging to the principal interval of the x-coordinates; a de Laval M-velocity is defined as at least one of said de Laval low M-velocity and said de Laval high M-velocity; the specifically shaped tunnel being adapted to said flowing fluid laminar motion with at least one of said Venturi M-velocity and said de Laval M-velocity; wherein walls of the specifically shaped tunnel is formed by at least one of: a solid material; streamlines of said flowing fluid being subjected to an action of solid surfaces; and streamlines of flowing said plasma being subjected to an action of a magnetic field.

3. An actually-airfoil body corpus comprising an actually-airfoil shape being such that, when a portion of ambien flow moving adjacent to a surface of the actually-airfoil corpus, the portion is further called: “said flowing fluid ambient-adjoining portion”, said flowing fluid ambient-adjoining portion inevitably becomes subjected to an action of the surface of the actually-airfoil corpus and thereby becomes shaped such that performing said flowing fluid inward portion flowing adjacent to one of the walls of the specifically shaped tunnel of claim 2, wherein, to further specify said actually-airfoil body corpus, a set of terms is defined as follows: (a) a biconvex airfoil profile is defined as an elongated closed contour in a sectional plane, wherein said elongated closed contour having: a rounded leading edge, an extremely sharp trailing end, and two opposite lengthened smoothly curved sides, joining said rounded leading edge and said sharp trailing end, and thereby forming said elongated closed contour, wherein each of said two opposite lengthened smoothly curved sides comprising at least one convex withers; (b) a local sagittal axis, associated with said biconvex airfoil profile, is defined as an imaginary axis oriented substantially tangentially to one of the two opposite lengthened smoothly curved sides nearby said extremely sharp trailing end; (c) said one of the walls being real and constructed from said solid material and wherein an opposite wall, which being opposite to said one of the walls being real and constructed from said solid material, being further specified as formed by streamlines of said flowing fluid, wherein said streamlines are that, which are bordering said flowing fluid ambient-adjoining portion; (d) said actually-airfoil shape of the body corpus is further specified as a shape, having said biconvex airfoil profile of a longitudinal section in said sectional plane; wherein each of said two opposite lengthened smoothly curved sides has a curvature of a wall of the specifically shaped tunnel and wherein, when the body is exposed to ambient flow and oriented relative to the ambient flow motion such that the rounded leading edge of the biconvex airfoil profile meets the ambient flow, portions of which moving ambient-adjoining the body corpus and flowing down from the extremely sharp trailing end, the direction of the ambient flow motion and said local sagittal axis are substantially collinear; and (e) the Coanda-effect is specified as a tendency of an ambient-adjoining portion of said flowing fluid to be attracted to and aligned with a nearby curved surface of said actually-airfoil body corpus, the tendency being accompanied by a varying of said flowing fluid ambient-adjoining portion's cross-sectional area as said flowing fluid ambient-adjoining portion moves in alignment with the nearby curved surface of said actually-airfoil body corpus; wherein said actually-airfoil body corpus comprising a sectional profile being said biconvex airfoil profile, thereby, said actually-airfoil body corpus providing for that, while said flowing fluid ambient-adjoining portions are flowing around the actually-airfoil body corpus and further when said flowing fluid ambient-adjoining portions are stalling at said extremely sharp trailing end of said biconvex airfoil profile, the surfaces of the actually-airfoil corpus, being real and constructed from said solid material and forming said lengthened smoothly curved sides of said biconvex airfoil profile comprising at least one convex withers, act on said flowing fluid ambient-adjoining portion by the Coanda-effect, thereby resulting in that: said flowing fluid ambient-adjoining portions being characterized by static pressure distributed along each of said two said opposite lengthened smoothly curved sides of said biconvex airfoil profile at least one of linearly and substantially gradually and thereby providing for a condition for a laminar motion of said flowing fluid ambient-adjoining portions along said opposite lengthened smoothly curved sides of said biconvex airfoil profile, and two opposite said flowing fluid ambient-adjoining portions moving adjacent said two opposite lengthened smoothly curved sides of said biconvex airfoil profile, correspondingly, when meeting downstream behind the actually-airfoil body corpus, being characterized by substantially equal and co-directional velocities and by at least one of equal and approximately equal static pressures, thereby providing for a condition for at most minor jumps of the static pressures and thereby for a laminar motion of said two opposite flowing fluid ambient-adjoining portions downstream behind the actually-airfoil body corpus, thereby, said two opposite flowing fluid ambient-adjoining portions, when joining together, forming a laminar outflowing jetstream.

4. An improved wind-turbine; wherein an actually-airfoil blade is defined as a blade having the actually-airfoil body corpus of claim 3; said improved wind-turbine comprising: an axle capable of a forced mechanic rotational motion, said axle oriented along a sagittal axis; a set of identical actually-airfoil blades attached to said axle; and an engine, capable of transforming power of said forced mechanic rotational motion of said axle into electric power; wherein each of said identical actually-airfoil blades having an asymmetrical sectional profile, said asymmetrical sectional profile being said biconvex airfoil profile with said two opposite lengthened smoothly curved convex sides differing in convexity, thereby, when said improved wind-turbine is exposed to airflow moving along said sagittal axis, providing for, a set of sub-portions of said oncoming airflow flowing around said set of identical actually-airfoil blades, correspondingly, and each said sub-portion of said set of sub-portions becoming divided between two jetstreams flowing adjacent to said two opposite lengthened smoothly curved convex sides, correspondingly, wherein each of said two opposite lengthened smoothly curved convex sides is shaped to act on each of said two adjacent jetstreams by the Coanda-effect, thereby: curving streamlines of each of said two adjacent jetstreams to form the specifically shaped tunnel of claim 3, said curving streamlines bordering said adjacent jetstream, wherein the x-axis, the local sagittal axis, and said sagittal axis are substantially collinear thereby providing reduction of an attack angle and thereby minimizing impact of said two jetstreams on said two opposite lengthened smoothly curved convex sides of said identical airfoil blades, correspondingly; causing arising of lift-forces acting on each of said identical airfoil blades, wherein all said asymmetrical sectional profiles being oriented to provide for a set of said lift-forces acting on said set of identical airfoil blades, correspondingly, in unison and thereby providing for said forced mechanic rotational motion of said axle at least one of clockwise and inverse-clockwise with respect to a frontal point of view; and when the M-velocity of at least one of said two jetstreams reaching said de Laval M-velocity and, when moving nearby said at least one convex withers, reaching the specific M-velocity, triggering the de Laval enhanced jet-effect; thus, said set of identical airfoil blades of said improved wind-turbine being configured to minimize the impact and to trigger at least one of the Coanda-effect and the de Laval enhanced jet-effect, both having the jet-effect nature, in the final analysis, to produce the electric power at the expense of said airflow warmth.

5. An elemental jet-booster; wherein said elemental jet-booster as a whole having the actually-airfoil body corpus of claim 3 comprising the specifically shaped tunnel of claim 3; thereby, when said elemental jet-booster as a whole being exposed to said flowing fluid, said flowing fluid becoming divided between said flowing fluid inward portion, moving through the specifically shaped tunnel and a flowing fluid outer portion, moving ambient-adjoining to outer surface of said elemental jet-booster's body corpus, wherein said outer portion is said flowing fluid ambient-adjoining portion and wherein at least said flowing fluid ambient-adjoining portion becoming subjected to the Coanda-effect operation; wherein said elemental jet-booster as a whole being further specified as having a configuration representing at least one of: a convergent-divergent jet-nozzle, having an overall shape being said actually-airfoil shape and having a through hole being the specifically shaped tunnel; a convergent funnel, comprising walls having said actually-airfoil profile, wherein said convergent funnel being a convergent part of the adapted convergent-divergent tunnel, thereby, when said flowing fluid inward portion moving through said convergent funnel with said de Laval M-velocity, said flowing fluid inward portion becoming subjected to said enhanced jet-effect, providing for said flowing fluid inward portion's varying cross-sectional area interrelating with said varying M-velocity of said flowing fluid inward portion by said equation of M-velocity satisfying a condition for gradual smoothing of distributions of said flowing fluid thermodynamic parameters along the x-axis, thereby: further said flowing fluid inward portion stalling at said extremely sharp trailing end of said airfoil profile and joining with said flowing fluid ambient-adjoining portion, forming said laminar outflowing jetstream as a part of said outflowing portion of said flowing fluid, moving laminarly and becoming convergent-divergent and bordered by imaginary laminar streamlines of said flowing fluid ambient-adjoining portion, satisfying the condition for the gradual smoothing of distributions of said flowing fluid thermodynamic parameters along the x-axis, and the specifically shaped tunnel becoming partially formed by said imaginary streamlines of said laminar outflowing jetstream; and the actually-airfoil body corpus of claim 3; wherein said actually-airfoil profile being a part of a wall of the adapted convergent-divergent tunnel, further specified as: providing the condition for the gradual smoothing of distributions of said flowing fluid thermodynamic parameters along said actually-airfoil profile adapted to said de Laval M-velocity of said flowing fluid inward portion, and having an opposite wall formed by said imaginary laminar streamlines where, thereby: inherently providing the condition for the gradual smoothing of distributions of said flowing fluid thermodynamic parameters along said airfoil profile, when said flowing fluid ambient-adjoining portion flowing around said actually-airfoil body corpus with said de Laval M-velocity, said flowing fluid ambient-adjoining portion becoming subjected to said enhanced jet-effect, providing for said flowing fluid ambient-adjoining portion's varying cross-sectional area interrelating with said varying de Laval M-velocity of said flowing fluid ambient-adjoining portion by said equation of M-velocity providing the condition of gradual smoothing of distributions of said flowing fluid thermodynamic parameters along said airfoil profile, the adapted convergent-divergent tunnel becoming formed by said imaginary streamlines of said flowing fluid ambient-adjoining portion, and said flowing fluid ambient-adjoining portion becoming identical to said flowing fluid inward portion; thereby, said actually-airfoil shape of said elemental jet-booster as a whole being at least one of: axis-symmetrical or mirror-symmetrical, thereby providing that said enhanced jet-effect resulting in an optimized reactive thrust-force applied to said actually-airfoil body corpus and directed to said rounded leading edge, and asymmetrical, having two opposite sides differing in convexity, thereby providing for said enhanced jet-effect resulting in an optimized both: reactive thrust-force applied to said actually-airfoil body corpus and directed to said rounded leading edge, and lift-force applied to said actually-airfoil body corpus and directed to that of said two opposite sides which being more convex.

6. An adiabatic aerodynamic system comprising a sequential multi-stage cascade of at least a certain number N of the elemental jet-boosters claimed in claim 5; wherein an overall arrangement of said sequential multi-stage cascade of said at least certain number N said elemental jet-boosters is along a smoothly curved locus; wherein said smoothly curved locus is at least one of a straight line and a curve; wherein said smoothly curved locus is at least one of unclosed and closed such that each pair of neighbor said elemental jet-boosters of said sequential multi-stage cascade comprises: an upstream previous elemental jet-booster and a downstream next elemental jet-booster, both oriented along said smoothly curved locus; wherein the upstream previous elemental jet-booster is located upstream afore the downstream next elemental jet-booster and wherein each two neighbor said elemental jet-boosters of said sequential multi-stage cascade are at least one of spatially-separated and unbrokenly-connected; wherein: an oncoming flow portion, associated with said elemental jet-booster, is defined as a portion of said flowing fluid, called a flowing fluid portion, running at said rounded leading edge of said actually-airfoil profile of said actually-airfoil body corpus of the elemental jet-booster; an outflowing convergent-divergent jetstream, associated with said elemental jet-booster, is defined as said flowing fluid portion, outflowing through said open outlet butt-end of said adapted convergent-divergent tunnel of the elemental jet-booster; an ambient-adjoining convergent-divergent jetstream, associated with a certain said elemental jet-booster, is defined as said flowing fluid portion, flowing around the certain elemental jet-booster; an upstream jet-booster as a whole is defined a set of said elemental jet-boosters being arranged upstream afore the certain elemental jet-booster; thereby, said flowing fluid portion, while moving with M-velocities lower than said de Laval low M-velocities, is subjected to the Venturi effect, originated by said upstream jet-booster as a whole, thereby resulting in an integral acceleration of said flowing fluid portion as said flowing fluid portion flowing around the upstream jet-booster as a whole; thereby, each downstream next elemental jet-booster is exposed to said oncoming flow portion, associated with the downstream next elemental jet-booster, comprising said outflowing convergent-divergent jetstream, associated with the upstream previous elemental jet-booster, and thereby intensifying an effect of convergence of said ambient-adjoining convergent-divergent jetstream and said outflowing convergent-divergent jetstream, both associated with the downstream next elemental jet-booster, wherein the certain number N is chosen to satisfy a condition under which, for said flowing fluid originally moving with said M-velocity lower than the specific M-velocity, the resulting operation of said sequential multi-stage cascade of at least N said elemental jet-boosters provides for that a sub-portion of said ambient-adjoining convergent-divergent jetstream, associated with at least one of said elemental jet-boosters, reaches the specific M-velocity while moving through the cross-section of minimal area corresponding to said ambient-adjoining convergent-divergent jetstream; thereby, said flowing fluid portion: when reaching said de Laval low M-velocity, is inevitably subjected to the de Laval jet-effect, resulting in said flowing fluid portion's divergent sub-portion said extra-acceleration and extra-cooling, and thereby resulting in motion with M-velocities higher than the specific M-velocity; and when reaching said de Laval high M-velocity, is subjected to the de Laval retarding-effect, resulting in said flowing fluid portion's said divergent sub-portion extra-slowing and extra-warming, and thereby resulting in motion with M-velocities lower than the specific M-velocity; wherein said smoothly curved locus is at least one of a straight line, an arc, a spiral of Archimedes, an outer helical outline of the Archimedean screw, a rounded contour, an ellipse, and a circumference; thus, said flowing fluid portion being subjected to sequentially cascaded disturbance as flowing around said sequential multi-stage cascade of at least N said elemental jet-boosters along said smoothly curved locus, thereby said sequentially cascaded disturbance causing an origination of corresponding sequentially cascaded acoustic waves in said flowing fluid, said acoustic waves being at least one of peculiar and forced; wherein said overall arrangement of said sequential multi-stage cascade of at least N said elemental jet-boosters along said smoothly curved locus provides for certain distances between at least N said elemental jet-boosters thereby providing at least one of: an at least partially in-phase superposition of said sequentially cascaded originated acoustic waves; and an at least partially anti-phase superposition of said sequentially cascaded originated acoustic waves; wherein: said adiabatic aerodynamic system is at least one of stationary and moving; said flowing fluid is at least one of natural and artificial; and said flowing fluid is at least one of airflow and streaming water.

7. An air cooler and vapor-to-water condenser; said air cooler and vapor-to-water condenser comprising the adiabatic aerodynamic system of claim 6, wherein said ambient flowing fluid is a humid airflow bringing water-vapor; wherein said flowing fluid portion, when originally moving with said M-velocity, lower than the specific M-velocity, being subjected to at least one of: the Venturi effect, resulting in said flowing fluid portion acceleration and cooling, and the de Laval jet-effect, resulting in said flowing fluid portion extra-acceleration and extra-cooling; thereby reaching the so-called dew-point temperature corresponding to the humidity of airflow, the temperature of said flowing fluid portion, reduced down to the dew-point temperature, inevitably triggers condensation of the water-vapor into airborne water-aerosols or drops of dew, sticking to an exposed body corpus surface.

8. A vortex generator comprising the adiabatic aerodynamic system of claim 6, wherein said closed smoothly curved locus is a circumference, thereby providing that said elemental jet-boosters of said sequential multi-stage cascade, arranged circumferentially, act on said flowing fluid portions with a sequentially multi-stage cascaded operation of the Coanda-effect reinforced multi-repeatedly in an adiabatic process, thereby aligning a motion of said flowing fluid portions with nearby actually-airfoil surfaces of said elemental jet-boosters, thereby resulting in that said ambient-adjoining convergent-divergent jetstreams become circulating ambient-adjoining convergent-divergent jetstreams, wherein said sub-portions of said circulating ambient-adjoining convergent-divergent jetstream, when moving with M-velocities lower than the specific M-velocity, are subjected to the Venturi effect in a positive feedback loop, thereby providing an acceleration of said sub-portions of said circulating ambient-adjoining convergent-divergent jetstreams in said positive feedback loop, thereby resulting in that said sub-portions of said circulating ambient-adjoining convergent-divergent jetstreams become moving with said de Laval M-velocities triggering alternating both: the de Laval jet-effect and the de Laval retarding-effect, thereby stabilizing an effective M-velocity alternating above and below the specific M-velocity.

9. An engine comprising the vortex generator of claim 8, wherein said engine is at least one of: an air cooler, wherein said ambient flowing fluid is natural air; a vapor-to-water condenser, wherein said ambient flowing fluid is humid air; an electricity generator further comprising a converter, transforming a kinetic power of said flowing fluid's molecules motion into electric power; wherein said converter is at least one of: a turbo-generator comprising a rotor and stator, primary transforming a kinetic power of said flowing fluid motion in a prevalent direction into electric power; and a Peltier element operating as a thermoelectric generator, primary producing electricity from temperature difference caused by a jet-effect, wherein said jet-effect is at least one of the Venturi effect, the de Laval jet-effect, and the de Laval retarding-effect; and an alternator comprising a detector of waves, transforming wave power of said in-phase superposed sequentially cascaded originated acoustic waves into electric power; a thrust-engine for a flying-saucer; said thrust-engine for said flying-saucer further comprising a set of airfoil wings; wherein said ambient flowing fluid is at least one of an artificial airflow and natural wind; and wherein said closed smoothly curved locus forming a closed contour placed in an imaginary so-called transversal plane; wherein said elemental jet-boosters having an effective height in a direction, perpendicular to said transversal plane, such that the vortex generator occupies an effective space in a form of a cylinder having: an oval base, parallel to said transversal plane comprising said closed smoothly curved locus, and a side of said effective height; wherein said circulating ambient-adjoining convergent-divergent jetstreams, associated with said elemental jet-boosters, contacting with said flowing fluid portions within said cylinder, and thereby drawing and circulating said flowing fluid portions within said cylinder; and wherein said airfoil wings are arranged within said cylinder and oriented to meet said flowing fluid portions circulating within said cylinder, wherein said actually-airfoil shape of at least one said oriented airfoil wing having said airfoil profile of said longitudinal section in said local sagittal plane, said at least one oriented airfoil wing being asymmetrical relative to said transversal plane, thereby causing a thrust-force, frequently called a lift-force, being perpendicular to said transversal plane.

10. A corpus of a fluid-repellent jet-gear, submerged in ambient fluid; wherein a phobic-repulsing jet-effect is defined as a kind of jet-effect, occurring in a fluid near to a surface made from a fluid-repellent material; wherein said kind of jet-effect occurring, when nearby fluid portions, contacting with the surface, become substantially subjected to a repelling action of phobic-repulsive van der Waals forces originated by the fluid-repellent material, wherein said repelling action being appeared as an acceleration of the nearby fluid portions; said acceleration occurring at the expense of said nearby fluid portions' internal heat energy, thereby said acceleration being inevitably accompanied by said nearby fluid portions' temperature decrease, thereby creating a temperature difference between an original temperature of said fluid's portions, yet to be subjected to said phobic-repulsing jet-effect, and a decreased temperature of said nearby fluid portions, already subjected to said phobic-repulsing jet-effect, and wherein said repelling action being at least one of an inherent property of the fluid-repellent material and controlled by an external power source; wherein said corpus of said fluid-repellent jet-gear, called also said fluid-repellent jet-gear corpus, comprising at least an outer layer, made from said fluid-repellent material; wherein said outer layer having a relief-structured surface, contacting with nearby portions of said fluid; wherein said relief-structured surface comprising asymmetrically shaped and co-oriented airfoil protrusions thereby providing a cumulative repelling action of said phobic-repulsive van der Waals forces on said nearby fluid portions in unison and co-oriented in a prevalent direction, thereby causing said nearby fluid portions motion in said prevalent direction; wherein said asymmetrically shaped and co-oriented airfoil protrusions having a form of at least one of saw-like teeth, curved cogs having concave sides with parabolic sectional profiles, teeth-like fins, fish-scales, humps, airfoil convexities, screwed blades, convex airfoil withers, and spiral turns; wherein an overall configuration of said fluid-repellent jet-gear corpus having a substantially-airfoil orientation, aligned to said prevalent direction; thereby, airfoil streamlines of said nearby fluid portions moving in said prevalent direction forming the specifically shaped tunnel of claim 2; wherein said overall configuration of said fluid-repellent jet-gear corpus is in a form of at least one of: a bar, shaped as saw, having said substantially-airfoil orientation along said bar; a wheel, shaped as circle-saw, having said substantially-airfoil orientation being at least one of clockwise and inverse-clockwise; a convex-concave configuration, wherein a convex side has said substantially-airfoil orientation, and a concave side comprises said outer layer, made from said fluid-repellent material; a spiral staircase, having said substantially-airfoil orientation along a helical contour; a screw of Archimedes, having airfoil turns; a set of streamlined wings; a propeller; and a capillary tube; wherein an inner side of said capillary tube comprising said outer layer, and wherein said airfoil protrusions, being asymmetrically shaped and co-oriented and located within said capillary tube, thereby providing said cumulative repelling action of said phobic-repulsive van der Waals forces on said nearby fluid portions, located within said capillary tube, in unison and co-directed along said capillary tube, thereby resulting in said nearby fluid portions motion along said prevalent direction along and within said capillary tube; wherein said asymmetrically shaped and co-oriented airfoil protrusions are at least one of stationary and rotating relative to said fluid-repellent jet-gear corpus; wherein said fluid-repellent jet-gear corpus is at least one of stationary and moving relative to said fluid's portions, yet to be subjected to said phobic-repulsing jet-effect; wherein said prevalent direction of said nearby fluid portions motion, being at least partially at least one of whirling, headway, and streaming along a helical trajectory; wherein said fluid is at least one of a water-based liquid, an oil-based liquid, an alcohol-based liquid, and an ionized gas or liquid; and wherein said fluid-repellent material being at least one of hydrophobic, oleophobic, omniphobic, and ion-repellent and being embodied as at least one of an omni-repellent heating component, a water-repellent permanent magnet, a plasma-repellent magnet, a plasma-repellent electrically charged surface, and a strongly-hydrophobic surface.

11. An enhanced fanjet engine comprising: the specifically shaped tunnel of claim 2, and a propelling compressor having a propeller capable of entrapping fluid matter.

12. An enhanced motionless jet-engine comprising: the specifically shaped tunnel of claim 2, and a motionless compressor of fluid matter, said motionless compressor being arranged upstream afore said open inlet butt-end of the specifically shaped tunnel; said motionless compressor being capable of compression a certain portion of said fluid matter to provide a pressure difference between the pressure of the certain portion of said fluid matter and another portion of said fluid matter, thereby triggering acceleration of the certain portion of said fluid matter, and thereby providing for reincarnation of the certain portion of said fluid matter into said flowing fluid inward portion moving with said varying velocity-vector characterized by said M-velocity being at least one of: (i) said Venturi M-velocity in said open outlet butt-end, and (ii) said de Laval low M-velocity to reach the specific M-velocity in said narrow throat at said critical condition point; wherein said motionless compressor being at least one of: a heating compressor comprising a heater of said fluid matter; a dragging compressor comprising a container inlet having a shape of a convergent funnel; and a gravity compressor comprising a container filled with said fluid matter characterized by said density higher than said density of ambient gas; said gravity container being submerged in a gravitational field, wherein a height is defined as a spatial interval along a prevalent direction of force-lines of the gravitational field, thereby, said fluid matter becoming characterized by said static pressure distributed in height; thus, said enhanced motionless jet-engine is further specified as at least one of: a motionless heating-jet engine comprising said heating compressor and the specifically shaped tunnel; a motionless dragging-jet engine comprising said dragging compressor and the specifically shaped tunnel; and a motionless gravity-jet engine comprising said gravity compressor and said container having the specifically shaped tunnel.

13. An aerodynamic device comprising the specifically shaped tunnel of claim 2, and an engine, arranged downstream behind said open outlet butt-end of the specifically shaped tunnel; said engine using said extra-accelerated and extra-cooled jetstream, outflowing through said open outlet butt-end; and wherein said engine is at least one of a jet-engine, a turbo-jet engine, a motor applied to a vehicle, a generator of electricity, a cooler, a Peltier element operating as thermoelectric generator, and a vapor-into-water condenser.

14. A two-stage adapted convergent-divergent tunnel comprising two open butt-ends: inlet, exposed to a flow, and outlet, by definition releasing an outflowing jetstream; said two-stage adapted convergent-divergent tunnel comprising two specifically shaped tunnels: first-stage and second-stage; each of the two specifically shaped tunnels: first-stage and second-stage, is as claimed in claim 2, wherein said flowing fluid is the flow; wherein said first-stage specifically shaped tunnel comprises two open butt-ends: a first-stage inlet and a first-stage outlet; and wherein said second-stage specifically shaped tunnel comprises two open butt-ends: a second-stage inlet and a second-stage outlet; and wherein said second-stage specifically shaped tunnel is arranged downstream behind said first-stage open outlet butt-end by superposing said second-stage open inlet butt-end with said first-stage open outlet butt-end, thereby forming said two-stage adapted convergent-divergent tunnel having two sequential major successive constituents: (a) said first-stage specifically shaped tunnel, having said first-stage inlet becoming identical with said open inlet butt-end, exposed to the flow; wherein a portion of the flow, as said flowing fluid inward portion, enters said first-stage specifically shaped tunnel moving through said first-stage open inlet butt-end with said de Laval high M-velocity, thereby providing a condition for the de Laval retarding-effect triggering, wherein said first-stage specifically shaped tunnel being suited for said values M of said de Laval M-velocity varying in said essential M-velocity range, thus, said values M relate with said x-coordinates x of said principal interval corresponding to said first-stage specifically shaped tunnel as a monotonic smooth function M.sub.1(x) having a negative partial derivation ∂M.sub.1(x)/∂x, and thereby resulting in an M-velocity of said portion of the flow at said open first-stage outlet butt-end becoming lower that the specific M-velocity; and (b) said second-stage specifically shaped tunnel, having said second-stage outlet becoming identical with said open outlet butt-end, releasing said outflowing jetstream; wherein said second-stage specifically shaped tunnel, meeting said portion of the flow, as said flowing fluid inward portion, moving through said second-stage open inlet butt-end with said M-velocity at said open first-stage outlet butt-end, wherein said second-stage specifically shaped tunnel being suited for said values M of said de Laval M-velocity varying in said essential M-velocity range comprising said M-velocity of said portion of the flow at said open first-stage outlet butt-end, said M-velocity of said portion of the flow at said open first-stage outlet butt-end thereby becoming said de Laval low M-velocity at said open second-stage inlet butt-end, thereby triggering the de Laval jet-effect; thus, said values M relate with said x-coordinates x of said principal interval corresponding to said second-stage specifically shaped tunnel as a monotonic smooth function M.sub.2(x) having a positive partial derivation ∂M.sub.2(x)/∂x.

15. A two-stage jet-booster, having a corpus with an outer overall airfoil shape and having the two-stage adapted convergent-divergent tunnel, according to claim 14; wherein said flowing fluid ambient-adjoining portion, flowing around said corpus of said two-stage jet-booster and thereby becoming subjected to an operation of the Coanda-effect; and wherein the two-stage adapted convergent-divergent tunnel is at least one of: real, inner, built-in into said two-stage jet-booster, having said real specifically shaped tunnel's walls; imaginary, outer, bordered by streamlines of said flowing fluid ambient-adjoining portion, flowing around a tandem arrangement of two airfoil bodies, each having a specifically shaped airfoil corpus having at most one convex withers, wherein said tandem arrangement of two airfoil bodies, together having at most two said convex withers, is such that said at most two convex withers of the two specifically shaped actually-airfoil body corpuses meet said flowing fluid ambient-adjoining portion sequentially, thereby resulting in a two-stage convergent-divergent varying of said flowing fluid ambient-adjoining portion's cross-sectional area as said flowing fluid ambient-adjoining portion sequentially passes over said at most two convex withers; wherein imaginary walls, formed by said streamlines, bordering said flowing fluid ambient-adjoining portion, constitute the two-stage adapted convergent-divergent tunnel, and wherein said flowing fluid ambient-adjoining portion is said flowing fluid inward portion moving through the two-stage adapted convergent-divergent tunnel; and imaginary, outer, formed by at least two opposite walls, namely: at least one side of said two-stage jet-booster corpus as real specifically shaped tunnel's wall having said outer airfoil shape being two-humped, comprising two sequentially arranged convex withers separated by a concavity and oriented such that said two convex withers meet said flowing fluid ambient-adjoining portion sequentially; and at least one imaginary said specifically shaped tunnel's wall, formed by streamlines of said flowing fluid ambient-adjoining portion, moving nearby and in alignment with said outer two-humped airfoil side of said two-stage jet-booster corpus; thereby providing that said flowing fluid ambient-adjoining portion is said flowing fluid inward portion moving through the two-stage adapted convergent-divergent tunnel.

16. A jet-transformer for transformation of fluid heat energy into electricity; said jet-transformer comprising: a vertically oriented pipe having the specifically shaped tunnel of claim 10; at least one laminar flow maker, having the corpus of said fluid-repellent jet-gear of claim 10, in turn, having a reflective parabolically-concave surface and being supplied by a heater located in the reflective parabolically-concave surface focus: to heat a portion of said fluid thereby triggering the fluid portion extension, and to provide the heated fluid portion motion in said prevalent direction being upward vertical; and the improved wind-turbine of claim 4, located within the specifically shaped tunnel.

17. The corpus of said fluid-repellent jet-gear of claim 10; wherein said fluid-repellent jet-gear corpus further having said actually-airfoil shape; wherein said fluid is ambient humid air composed of ambient dry air and ambient water vapor; wherein said fluid-repellent material is a hydrophobic material; wherein said hydrophobic material further being porous, thereby providing that small portions of said ambient dry air penetrating into said porous material and thereby becoming inherent portions of said outer layer and thus originating two features: on the one hand, said portions of said ambient dry air, as said inherent portions of said outer layer, make said outer layer becoming more inert to said ambient dry air, and on the other hand, said hydrophobic material prevents said outer of said porous material from filling by water condensed from natural humid air, thereby said two features providing a decrease of a skin-friction effect; wherein said hydrophobic and porous material is at least one of fuzz, a sponge, and a fibrous structure, and wherein said hydrophobic and porous material is at least one of natural and artificial.

18. A hydrophobic jet-device; wherein a complex corpus of said hydrophobic jet-device comprising a set of sub-corpuses; wherein each said sub-corpus of said complex corpus is the corpus of said fluid-repellent jet-gear of claim 10; said hydrophobic jet-device comprising a power converter; wherein said power converter is further specified as being at least one of: a turbo-generator, wherein a rotor-subset is defined as a subset of said set of sub-corpuses, said subset comprising said sub-corpuses repelling said nearby fluid portions in at least one of said clockwise and said inverse-clockwise direction; said turbo-generator having a rotor, powered by motion of said rotor-subset; wherein said turbo-generator primary transforming a kinetic power of said nearby fluid portions motion in said prevalent direction into electric power; a Peltier element operating as a thermoelectric generator, primary producing electricity from the temperature difference caused by said phobic-repulsing jet-effect; wherein a “cold” side of the Peltier element being submerged in said nearby fluid portions being already subjected to said phobic-repulsing jet-effect and thereby cooled having said decreased temperature, while a “hot” side of the Peltier element being submerged in said fluid's portions, yet to be subjected to said phobic-repulsing jet-effect and so having said original temperature; and an ice-maker, wherein said fluid is seawater being subjected to the generalized jet-effect provided by said generalized trigger of jet-effect and thereby the seawater being cooled and further frozen due to the triggered generalized jet-effect; and wherein said fluid is at least one of a permanently refreshed warm fluid having said original temperature and a fluid permanently consuming caloric.

19. A motionless magnet-jet engine comprising: a core having a specifically shaped corpus made from an electro-conductive and magneto-boosting material, wherein the specifically shaped corpus is the specifically shaped tunnel of claim 2 for electron gas composed of free electrons of said electro-conductive and magneto-boosting material, and a motionless magnetizing compressor of fluid matter; wherein: said electro-conductive and magneto-boosting material being as at least one of: ferromagnetic and ferrimagnetic, characterized by a high magnetic permeability; said specifically shaped core corpus comprising at least two portions: relatively thick and relatively thin, differing in cross-sectional area, such that the cross-sectional area of said relatively thick portion is bigger than the cross-sectional area of said relatively thin portion by a factor of at least 1.05; said fluid matter is further specified as said electron gas, and so said flowing fluid is further specified as induced eddy current, being induced within said electro-conductive and magneto-boosting material and performing a circular motion of the electron gas along a certain closed trajectory bordering a portion of a cross-sectional plane within said core; said flowing fluid portion is further specified as an annular portion of the electron gas moving as a whole along said certain closed trajectory with an angular-velocity-vector relative to the specifically shaped core corpus, thereby, said flowing fluid portion performing an annular portion of said induced eddy current, wherein the angular-velocity-vector of said flowing fluid portion, being vectored along a normal to said cross-sectional plane within said core; said varying velocity-vector is further specified as said angular-velocity-vector of said flowing fluid portion; a streamline of said induced eddy current is defined as a curve aligned with said angular-velocity-vectors of said flowing fluid portions within and along said specifically shaped core corpus; a magnetic field strength, induced and boosted within said electro-conductive and magneto-boosting material, is defined as magnetic field strength, associated with and accompanied by said induced eddy current; said magnetic field strength being characterized by a relative concentration of magnetic field strength force-lines being aligned with said induced eddy current streamlines; and said motionless magnetizing compressor comprising: at least one said relatively thick portion of said specifically shaped core corpus; and an input electro-conductive-coil winding encircling at least said relatively thick portion of the specifically shaped core corpus; wherein said input electro-conductive-coil winding being electrically connected to a source of electrical voltage and so bringing electrical current to create said magnetic field strength being induced and boosted within the electro-conductive and magneto-boosting material of the specifically shaped core corpus, wherein said induced and boosted magnetic field strength being inherently accompanied by said induced eddy current; thereby, said angular-velocity-vector of said induced eddy current, being gradually-varying along and remaining aligned with said specifically shaped core corpus; said gradually-varying angular-velocity-vector of said induced eddy current being interrelated with gradually-varying said relative concentration of said associated magnetic field strength force-lines; and the relative concentration of the associated magnetic field strength force-lines in said relatively thin portion of the specifically shaped core corpus being higher than the relative concentration of the associated magnetic field strength force-lines in said relatively thick portion of the specifically shaped core corpus in accordance with the equation of continuity; and, thereby, said motionless magnet-jet engine providing for an increase of the relative concentration of the magnetic field strength force-lines crossing said cross-sectional area of said relatively thin portion of the specifically shaped core corpus.

20. An elemental enhanced transformer of alternating electrical voltage and current; wherein said elemental enhanced transformer comprising the motionless magnet-jet engine of claim 19, wherein: the source of electrical voltage being further specified as a source of an alternating electrical voltage; the induced eddy current being further specified as alternating; the induced magnetic field being further specified as alternating; the velocity-vector is further specified as a measure of an alternating angular-velocity of the induced alternating eddy current; wherein said alternating angular-velocity being in a range corresponding to said Venturi M-velocities relative to said convergent-divergent core corpus made from said electro-conductive and magneto-boosting material; said convergent-divergent core corpus being further specified as having a closed toroidal-like convergent-divergent shape; wherein said electro-conductive and magneto-boosting material being further specified as characterized by low coercivity; thereby, said convergent-divergent core corpus performing a closed shaped tunnel for said alternating induced magnetic field; wherein said closed toroidal-like shaped convergent-divergent core corpus being gradually tapered to have: a relatively thick portion, characterized by a relatively wide cross-section of the closed toroidal-like shaped convergent-divergent core corpus, and a relatively thin portion, characterized by a relatively narrow cross-section of the closed toroidal-like shaped convergent-divergent core corpus; wherein the magnetizing compressor is further specified as comprising: said further specified convergent-divergent core corpus having said closed toroidal-like convergent-divergent shape; and at least two mutually-isolated electro-conductive-coils: said input winding and an output winding, each encircling said closed toroidal-like shaped convergent-divergent core corpus, wherein: said input electro-conductive-coil winding encircling said relatively thick portion of said shaped convergent-divergent core corpus and being electrically connected to said source of said alternating electrical voltage, and said output electro-conductive-coil winding encircling said relatively thin portion of said closed toroidal-like shaped convergent-divergent core corpus and being electrically connected to an electrical load.

21. A complicated enhanced transformer of alternating electrical voltage and current comprising at least two electrically inter-connected said elemental enhanced transformers of alternating electrical voltage and current of claim 20, further called: previous elemental enhanced transformer, and next elemental enhanced transformer, correspondingly; wherein the output electro-conductive-coil winding of the previous elemental enhanced transformer being electrically connected to the input electro-conductive-coil winding of the next elemental enhanced transformer, thereby, the output electro-conductive-coil winding of the previous elemental enhanced transformer being said source of electrical voltage applied to the input electro-conductive-coil winding of the next elemental enhanced transformer; and the input electro-conductive-coil winding of the next elemental enhanced transformer being said electrical load applied to the output electro-conductive-coil winding of the previous elemental enhanced transformer.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) In order to understand the invention and to see how it may be carried out in practice, a preferred embodiment will now be described, by way of a non-limiting example only, with reference to the accompanying drawings, in the drawings:

(2) FIG. 1a is a prior art schematic drawing of chiral molecules;

(3) FIG. 1b is a prior art schematic drawing of the convergent-divergent Venturi tube;

(4) FIG. 1c is a prior art schematic view of the convergent-divergent de Laval nozzle;

(5) FIG. 1d is a prior art schematic illustration graphics of gas velocity, static pressure, and temperature distributions within the de Laval convergent-divergent jet-nozzle;

(6) FIG. 1e is a schematic drawing of a prior art ordinary blowing ventilator;

(7) FIG. 1f is a prior art schematic drawing of a body blown by an airflow portion;

(8) FIG. 1g is a schematic drawing of a classical prior art profile of an airplane wing;

(9) FIG. 1h is a schematic drawing of considerable amounts of water-aerosols and micro-flakes-of-snow, which are observed behind the high-speed aircraft's wings;

(10) FIG. 1i is a prior art schematic illustration of points of sail;

(11) FIG. 1k is a prior art schematic illustration of a wind turbine, built-in into a cylinder;

(12) FIG. 1l is a prior art schematic illustration of the Ranque-Hilsch vortex tube;

(13) FIG. 1m is a prior art schematic illustration of the Beverley Clock;

(14) FIG. 2 is a prior art schematic illustration of fluid motion in an imaginary flow tube;

(15) FIG. 3 is a prior art schematic illustration of fluid motion in a real pipe;

(16) FIG. 4 is a schematic illustration of a box having two modules;

(17) FIG. 5a is a schematic illustration of a small portion of fluid;

(18) FIG. 5b is a schematic illustration of a fluid small portion adjacent to a body;

(19) FIG. 5c is a schematic illustration of a fish's squama surface fragment hypothetical interpretation, in accordance with the principles of the present invention;

(20) FIG. 5d is an illustration of a shaped body made from a hydrophobic material and submerged in water;

(21) FIG. 5e is a schematic illustration of a convex-concave corpus.

(22) FIG. 5f is a schematic illustration of a wheel-gear-like configured overall shape, having a sectional profile similar to a circle-saw, comprising fragments made from a hydrophobic material;

(23) FIG. 5g is an illustration of an exemplary aggregation comprising a set of many hydrophobic jet-gears;

(24) FIG. 5h is a schematic isometry of a hydrophobic-propeller submerged in water;

(25) FIG. 5i is a schematic illustration of a hydrophobic-spiral;

(26) FIG. 5j is a schematic isometry of a pair of hydrophobic-propellers operating as hydrophobic-engine;

(27) FIG. 5k is a schematic illustration of a pair of unbroken spirals;

(28) FIG. 5l illustrates an exemplary embodiment of constructive interference of electromagnetic waves;

(29) FIG. 5m is a schematic illustration of a generalized generator;

(30) FIG. 5n is a schematic illustration of a motionless gravity-jet engine;

(31) FIG. 5o is a schematic illustration of two transformers of alternating electrical voltage and current;

(32) FIG. 6a is a schematic illustration of an optimized convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(33) FIG. 6b is a graphical representation of air velocity, static pressure, and temperature distributions along an optimized convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(34) FIG. 6c is a schematic illustration of an exemplary profile of an optimized tunnel;

(35) FIG. 6d is a schematic illustration of an exemplary profile of an optimized tunnel;

(36) FIG. 6e is a schematic illustration of an exemplary profile of an optimized tunnel;

(37) FIG. 6f is a schematic illustration of an optimized inverse convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(38) FIG. 6g is a graphical representation of air velocity, static pressure, and temperature distributions along an optimized inverse convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(39) FIG. 6h is a schematic illustration of a two-stage convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(40) FIG. 7a shows comparative graphs of the dependencies of the nozzle extension ratio vs. the airflow M-velocity, calculated by the classical and suggested models;

(41) FIG. 7b is a schematic illustration of a compressor supplied by an optimized convergent-divergent jet-nozzle, constructed according to the principles of the present invention;

(42) FIG. 7c is a schematic sectional view of a flying capsule, constructed according to the principles of the present invention;

(43) FIG. 7d is a schematic sectional view of a flying capsule, constructed according to the principles of the present invention;

(44) FIG. 7e is a schematic drawing of an improved blowing propeller, constructed according to the principles of the present invention;

(45) FIG. 7f is a schematic drawing of an improved sucking propeller, constructed according to the principles of the present invention;

(46) FIG. 8a is a schematic illustration of an actually-airfoil wing blown by wind;

(47) FIG. 8b is a schematic illustration of a flying airfoil body;

(48) FIG. 8c is a schematic illustration of a flying airfoil body;

(49) FIG. 8d is a schematic illustration of flying arranged airfoil bodies;

(50) FIG. 9a is a schematic illustration of a sequential cascade of airfoil bodies;

(51) FIG. 9b is a schematic illustration of an in-line cascade of rings having airfoil walls;

(52) FIG. 9c is a schematic illustration of two Archimedean screws having airfoil walls;

(53) FIG. 9d is a schematic illustration of a circulating cascade of airfoil bodies;

(54) FIG. 9e is a schematic illustration of airfoil rings, arranged circumferentially;

(55) FIG. 9f is an adiabatic aerodynamic system comprising airfoil rings, arranged circumferentially, and wings, providing a lift-force;

(56) FIG. 9g is a schematic drawing of an improved wind-turbine, constructed according to the principles of the present invention;

(57) FIG. 9h is schematic side and front views of an improved wind-turbine;

(58) FIG. 9i is a schematic illustration of a jet-transformer, constructed according to the principles of the present invention;

(59) FIG. 10 is a schematic illustration of a block-diagram of the suggested method according to the principles of the present invention; and

(60) FIG. 11 is a table showing several equations.

(61) All the above and other characteristics and advantages of the invention will be further understood through the following illustrative and non-limitative description of preferred embodiments thereof.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

(62) The principles and operation of a method and an apparatus according to the present invention may be better understood with reference to the drawings and the accompanying description, it being understood that these drawings are given for illustrative purposes only and are not meant to be limiting. The detailed description of the preferred embodiments is divided between two paragraphs: “Generalized Equations of Molecular Fluid Motion” and “Jet-Effect Embodiments”, each having sub-paragraphs.

Generalized Equations of Molecular Fluid Motion

(63) FIG. 4 is a schematic illustration of an ideal thermo-isolated box 400, having two modules 401 and 402, separated by an ideal wall 403 having no weight, being freely-movable and easily-deformable. Thus, wall 403 may freely change the shapes and volume proportions of modules 401 and 402. Modules 401 and 402 are filled with portions of the same gas, having the same static pressure P.sub.401=P.sub.402, but different densities ρ.sub.401>ρ.sub.402 and absolute temperatures T.sub.401<T.sub.402, such that satisfying the condition ρ.sub.401T.sub.401=ρ.sub.402T.sub.402. It is expected that separating wall 403 will not move and will be not deformed because the static pressures P.sub.401 and P.sub.402 on both sides of wall 403 are identical. However, if wall 403 is withdrawn, then diffusion will start. This imaginary experiment says that the presence or absence of isolating wall 403 changes the situation, and the two neighboring portions of gas could accelerate each other by osmotic-like pressures if the portions have the same static pressure and differ in density and temperature. Modelling a molecular fluid as aggregated from many stationary and moving small-portions, the described hereinbelow interpretation of the molecular fluid portions' boundaries as sensitive to the temperature and density of surroundings as soon as the boundaries consist of the same molecular matter as the considered fluid, is one of the primary teachings of the present invention.

(64) FIG. 5a is a schematic illustration of a small portion of molecular fluid, for simplicity, having the shape of a cubic portion 500. Cubic portion 500 occupies the space defined by point coordinates 501(x, y, z), 502(x+Δx, y, z), 503(x, y+Δy, z), and 504(x, y, z+Δz), where Δx, Δy, and Δz are the distances between points 501 and 502, 501 and 503, and 501 and 504 correspondingly. Small portion 500 is composed of molecules moving randomly and in a prevalent direction, i.e. portion 500 is sufficiently small, such that having no a group of molecules whirling and making a complete rotating cycle within portion 500. Consider the cumulative force acting on portion 500. In the absence of gravitational forces, the fluid inner-static-pressure at any point of the fluid is the same in any direction; and the cumulative force on cubic portion 500, is defined by the fluid inner-static-pressure change from point to point. For simplicity, let the pressure change in the direction of the x-axis 505 only. The pressure on the left face, having points 501(x, y, z), 503(x, y+Δy, z), and 504(x, y, z+Δz), makes the force 506 equal to P.sub.inΔyΔz, where P.sub.in is the fluid inner-static-pressure at the left face from outside of cubic portion 500; and the fluid inner-static-pressure on the opposite right face makes the force 507 equal to −[P.sub.in+(∂P.sub.in/∂x)Δx]ΔyΔz. Therefore, the resulting force is −(∂P.sub.in/∂x)ΔxΔyΔz. If one also assumes that the fluid inner-static-pressure changes in the two remaining orthogonal directions, one can see that the pressure cumulative force per unit volume is −∇P.sub.in, where ∇ is the vector differential operator. The spatial change of the molecular fluid inner-static-pressure P.sub.in must be considered as interrelated with the molecular fluid density ρ and absolute temperature T variations in accordance with the thermodynamic and kinetic theory of matter.

(65) A generalized method for modeling an equation of fluid motion, wherein the fluid molecular structure is taken into the account, is a subject of the present invention.

(66) Inner Pressure and Momentum Conservation

(67) Considering fluid portion 500, occupying a certain volume V, the Newton Second Law or the conservation of momentum says that the cumulative force acting on portion 500, i.e. the variation of the momentum in the volume, must be due to the inflow or outflow of momentum through the closed surface S of portion 500 plus the forces acting on portion 500 by the fluid surrounding:

(68) $\begin{matrix} \frac{\partial}{\partial t} \int ρ udV = - \oint_{S} ρ uu .Math. ndS - \oint_{S} PndS, & Eq . (5.1) \end{matrix}$
where dS is the surface differential, n is the unit vector normal to surface differential dS, and ρ, u, and P are functions of spatial coordinates; wherein ρ is the fluid portion 500 density, u is the fluid portion 500 velocity-vector having absolute value u and being a measure of the molecular fluid molecules motion in a prevalent direction in addition to the random Brownian motion, and P is the cumulative-inner-static-pressure acting on the boundaries of portion 500; wherein in contrast to the classic approach of continuum mechanics, the fluid portion 500's boundaries have a molecular structure, and P is as a thermodynamic parameter interrelated with the fluid temperature, density, and gravity. The kinetic theory of ideal gases defines this relation for a stationary case in the absence of gravity as P.sub.ideal=NkT.sub.s/V.sub.s, where P.sub.ideal is the static pressure of an ideal gas, V.sub.s is the considered volume, N is the number of molecules in considered portion 500 of the ideal gas, k is the Boltzmann constant, and T.sub.s is the absolute temperature of the stationary ideal gas. The interrelation between thermodynamic parameters in the case of a hypothetical ideal gas can also be represented by the Clapeyron-Mendeleev gas law: P.sub.ideal=ρ.sub.sR.sub.0T.sub.s/μ, where ρ.sub.s is the stationary ideal gas density, R.sub.0 is the universal gas constant, and μ is the molar mass of the gas. Considering a real gas, the van der Waals approach bonds the static pressure of real gas P.sub.Waals acting on a stationary wall with the static pressure P.sub.ideal defined in the kinetic theory of ideal gas, namely:

(69) $\begin{matrix} P_{ideal} = (P_{Waals} + \frac{a}{V_{s}^{2}}) \frac{V_{s} - b}{V_{s}}, & Eq . (5.2 a) \end{matrix}$
where P.sub.Waals is the van der Waals static pressure of real gas, acting on a stationary wall; constant b has the physical sense of excluded volume because of the presence of the particles in the volume; and constant α defines the attraction forces between the real gas molecules. So, the van der Waals equation of state for real gas is written as:

(70) $\begin{matrix} (P_{Waals} + \frac{a}{V_{s}^{2}}) \frac{V_{s} - b}{V_{s}} = \frac{ρ_{s} R_{0} T_{s}}{μ}, & Eq . (5.2 b) \end{matrix}$

(71) The general enough theory of molecular fluid by van der Waals is qualitatively reasonable for the liquids as well. For the purposes of the present patent application, the van der Waals equation (5.2b) should be understood in a wider sense, allowing for the van der Waals parameters a and b to be variable, thereby making the equation (5.2b) appropriate for rigorous quantitative calculations applied to both: real gases and liquids, and thereby, generalizing the van der Waals equation of state for a molecular fluid.

(72) In contrast to the defined pressure P.sub.Waals acting on a stationary wall, being hypothetically inert to the fluid's molecules forces, i.e. being not phobic with repulsive forces and not sticking with attractive forces, the cumulative-inner-static-pressure P in equation (5.1) is acting on the fluid portion 500's boundaries, which, on the one hand, have the same inter-molecular attraction properties as the surrounding matter, and, on the other hand, may be not stationary, but be subjected to deformations and acceleration.

(73) In the absence of gravitational forces, when portion 500 is sufficiently far from a body having real walls, when portion 500, as stationary-small-portion, is not subjected to any acceleration and is affected by a stationary-effect only, the static pressure in equation (5.1) has the meaning of the inner-stationary-static-pressure defined for the static case. This pressure, indicated by P.sub.s, as a measure of the fluid molecules cumulative stationary-impact on imaginary boundaries of stationary-small-portion 500, is expressed as the following stationary equation:

(74) $\begin{matrix} P_{s} = P_{Waals} + \frac{a}{V_{s}^{2}} . & Eq . (5.2 c) \end{matrix}$
Taking into the account equation (5.2c), the van der Waals equation (5.2b), written in the form expressing the inner-stationary-static-pressure, takes the following form:

(75) $\begin{matrix} P_{s} = \frac{ρ_{s} r_{s} R_{0} T_{s}}{μ}, & Eq . (5.2 d) \end{matrix}$
where r.sub.s is the compression ratio V.sub.s/(V.sub.s−b), which represents how much the real fluid is compressed in comparison with a hypothetical ideal gas. For example, the assumption that the parameter b, quantifying the excluded volume, equals V.sub.s leads to the infinite compression ratio r.sub.s that corresponds to a hypothetical absolutely incompressible liquid. Equation (5.2d) allows considering the real fluid's inner-stationary-static-pressure P.sub.s as the static pressure of the ideal-like gas having specific fluid constant R.sub.s defined as R.sub.s=r.sub.sR.sub.0/μ.

(76) Taking into the consideration the definitions of the inner-stationary-static-pressure P.sub.s, compression ratio r.sub.s, and real molecular fluid as the ideal-like gas having specific fluid constant R.sub.s, the van der Waals equation of state for a molecular fluid, written in the form expressing the inner-stationary-static-pressure, gets the form, similar to the Clapeyron-Mendeleev gas law, namely:
P.sub.s=ρ.sub.sR.sub.sT.sub.s Eq. (5.2e).

(77) In the case of an ideal gas, the sense of stationary equation (5.2e) becomes identical with the Clapeyron-Mendeleev gas law.

(78) The value R.sub.sT.sub.s has the physical sense of the characteristic heat portion per unit mass, indicated by Q.sub.s, stored in fluid stationary-small-portion 500's molecular Brownian random motion, related to degrees of freedom causing the fluid molecules cumulative stationary-impact defining the inner-stationary-static-pressure P.sub.s, and satisfying equation (5.2e), namely: Q.sub.s=R.sub.sT.sub.s=P.sub.s/ρ.sub.s, and P.sub.s=ρ.sub.sQ.sub.s. The defined pressure P.sub.s can be decomposed into the following three components: the static pressure P.sub.ideal defined in the kinetic theory of ideal gas, and two additive partial components defining the molecular fluid compression depending on the van der Waals parameters a and b. The two additive partial components are: compression pressure-a, indicated by P.sub.a, and compression pressure-b, indicated by P.sub.b. The indexes a and b are associated with the van der Waals parameters a and b correspondingly. I.e. pressure P.sub.s is expressed as:
P.sub.s=P.sub.ideal+P.sub.a+P.sub.b Eq. (5.20.

(79) The partial compression pressure-b P.sub.b is defined as a measure of a compression-impact-effect, caused because of increased density of the molecular fluid, sufficient to take into account the compression ratio r.sub.s=V.sub.s/(V.sub.s−b). This is a pressure deforming the shape of fluid portion 500.

(80) The partial compression pressure-a P.sub.a is defined as a measure of a further deep-compression-effect, arisen because of increased density of the molecular fluid, sufficient to have to take into account the inter-molecular forces defined by the van der Waals parameter a, defining the potential energy of the inter-molecular attraction. The partial compression pressure-a P.sub.a interrelates with the potential energy of the inter-molecular attraction as:

(81) $\begin{matrix} U = \frac{P_{a}}{ρ_{s}}, & Eq . (5.2 g) \end{matrix}$
where U is the internal inter-molecular potential-energy-per-unit-mass. Thereby: while the molecular fluid is as an ideal gas, both: the partial compression pressure-a and the partial compression pressure-b equal zero: P.sub.a=0 and P.sub.b=0; if the molecular fluid is as a solid-gas with the compression ratio r.sub.s noticeably greater than 1 and with a minor influence of the inter-molecular attractive forces, the partial compression pressure-a is marginal: P.sub.a=0; and if the molecular fluid is as a liquid, the partial compression pressure-a decisively defines potential energy of the inter-molecular attraction.

(82) The fluid's density, on the one hand, has the sense of a measure of concentration and mass of the fluid molecules and, on the one hand, has the gravitational sense. The potential gravitational energy stored in the fluid portion unit mass in the Earth's gravitational field is G=zg, where z is the effective height of the fluid's portion above the Earth's ocean surface level. The partial potential-static-pressure P.sub.z distributed on height and provided by the Earth's gravitational field is added, namely:
P.sub.z=zρg=ρG Eq. (5.2),
where ρ is the fluid density that in the stationary case is ρ.sub.s satisfying stationary equation (5.2e).

(83) Reference is now made to FIG. 5b, a schematic illustration of a fluid portion 510 as a generalized case of fluid portion 500 of FIG. 5a such that having boundaries adjacent to the stationary walls of body 511. The approach described referring to FIG. 5a can be further adapted to an imaginary boundary layer, comprising fluid portion 510, moving near the real walls of body 511 and being subjected to deformations and acceleration.

(84) The adaptation involves a definition of the inner-static-pressure P.sub.in provided by the fluid molecules interactions as comprising two items: P.sub.in=P.sub.s+P.sub.boundary, where P.sub.boundary is the partial inner-boundary-layer-static-pressure. On the one hand, the partial inner-boundary-layer-static-pressure P.sub.boundary enforces the movement to be in alignment with the adjacent stationary walls of body 511, i.e. acting as a drag, and on the other hand, it results in the fluid's specific velocity distribution in an imaginary boundary layer, i.e. acting as a partial pressure relating to a viscous skin-friction effect. This is formalized as
P.sub.boundary=P.sub.drag+P.sub.viscous Eq. (5.3a),
where P.sub.drag is the partial drag-static-pressure acting on moving-small-portion 510, defined as the partial pressure, which arises when fluid portion 510 gets a convective acceleration redirecting moving-small-portion 510, sliding in alignment with the curvature of the real walls; and P.sub.viscous is the partial viscous-static-pressure acting on moving-small-portion 510, defined as the partial pressure, which results in that the velocity of moving-small-portion 510 is subjected to a specific spatial distribution in the imaginary boundary layer adjacent to the real walls of body 511. Here and further on, it is assumed that the interaction between the walls and fluid occurs without the heat energy exchange between the walls and fluid, so moving-small-portion 510 is undergoing a reversible adiabatic process.

(85) The partial drag-static-pressure P.sub.drag represents either phobic, i.e. fluid-repellent pressure, interrelated with phobic-repulsive forces directed inward fluid portion 510, or sticking pressure, related with attractive forces directed outward fluid portion 510, when the motion trajectory of fluid portion 510 is aligned with the wall's curvature or, more generally, with the trajectory of the adjusted portions of the moving fluid. The partial drag-static-pressure P.sub.drag defines the arisen boundary level effect arising due to the curvature of the walls. The partial drag-static-pressure P.sub.drag relates to the two mechanisms of fluid portion 510 acceleration: on the one hand, the partial drag-static-pressure P.sub.drag acts as a compressor-expander stagnating fluid portion 510; and on the other hand, the partial drag-static-pressure P.sub.drag acts to change the cross-sectional area of moving-small-portion 510.

(86) The effect of fluid portion 510 stagnating is formalized by the sum of the partial stagnation pressures: stagnation pressure-b, indicated by δP.sub.b, and of the deep-stagnation pressure-a, indicated by δP.sub.a. The indexes a and bare associated with relative variations of the van der Waals parameters a and b correspondingly.

(87) The partial stagnation pressure-b δP.sub.b is defined as a measure of a stagnation-impact-effect, i.e. of an effect of a cumulative stagnation-impact of the fluid molecules on the imaginary boundaries of fluid portion 510. This is a pressure deforming the shape of fluid portion 510. The partial stagnation pressure-b δP.sub.b is interrelated with a change of the moving-small-portion 510's volume V and, thereby, of the compression ratio r defined as V/(V−b), while retaining the same inter-molecular forces defined by van der Waals parameter a. The value r, now differing from the value r.sub.s defined for a stationary case, specifies the partial stagnation pressure-b δP.sub.b.

(88) The partial deep-stagnation pressure-a δP.sub.a is defined as a measure of a further deep-stagnation-effect, observed as further deformation of the shape of fluid portion 510, such that resulting in quantitative changes of the inter-molecular forces defined by the van der Waals parameter a, allowed to be variable. If the van der Waals parameter a is associated with the stationary-small-portion 500, subjected to the deep-compression-effect and yet to be subjected to the deep-stagnation-effect, then, considering the moving-small-portion 510, the variation, indicated by δa, is added, such that the van der Waals parameter a+δa corresponds to the moving-small-portion, subjected to the deep-stagnation-effect.

(89) For example, while the molecular fluid is as an ideal gas, both: the partial deep-stagnation pressure-a and the partial stagnation pressure-b equal zero: δP.sub.a=0 and δP.sub.b=0; if the molecular fluid is as a solid-gas with the variable compression ratio r and with minor variations of the inter-molecular attractive forces, the partial deep-stagnation pressure-a is marginal: δP.sub.a=0; and by contrast, if the molecular fluid is liquid, the partial stagnation pressure-b is negligible: δP.sub.b=0.

(90) The aspect of the partial drag-static-pressure P.sub.drag, associated with the change of the cross-sectional area of moving-small-portion 510 thereby providing fluid portion 510's sliding motion in alignment with the stationary walls curvature, is formalized as the partial pressure-c indicated by δP.sub.c. The partial pressure-c δP.sub.c interrelates with the Coanda-effect and is a measure of the cumulative aligning-impact of the fluid molecules on the imaginary boundaries of fluid portion 510 moving in the imaginary boundary layer adjacent to stationary walls of body 511.

(91) Thus, a drag-effect is the cumulative effect comprising: the stagnation-impact-effect providing the partial stagnation pressure-b, the deep-stagnation-effect providing the partial stagnation pressure-a, and the Coanda-effect providing the partial pressure-c;
such that the partial drag-static-pressure δP.sub.drag is quantified as equal to the sum, comprising three items, as expressed by:
δP.sub.drag=δP.sub.a+δP.sub.b+δP.sub.c Eq. (5.3b).

(92) The mentioned mechanisms, related to the partial pressures b and c, provide reversible adiabatic conversion of the kinetic energy of the fluid's molecules Brownian random motion into the kinetic energy of fluid portion 510's aligned motion, and vice-versa.

(93) The mentioned mechanism, related to the partial deep-stagnation pressure-a, changes the internal inter-molecular potential-energy-per-unit-mass by a value equal to

(94) $\begin{matrix} δ U = \frac{δ P_{a}}{ρ_{s}} & Eq . (5.3) \end{matrix}$
distributed in space.

(95) The partial viscous-static-pressure P.sub.viscous relates to the two mechanisms of fluid portion 510 acceleration: on the one hand, it is a skin-friction effect observed as an effect of the moving fluid's molecules sticking to the real walls; and on the other hand, it is an osmotic-like effect, which arises between the fluid's adjacent portions differing in either density or temperature.

(96) The partial skin-friction static-pressure P.sub.skin is a measure, how much the walls are sticky for the molecular fluid motion. This can be formalized as

(97) $\begin{matrix} P_{skin} = \frac{a_{w} - a - δ a}{V^{2}} \times F_{skin} (u, a + δ a, y_{w}), & Eq . (5.4 a) \end{matrix}$
where δa is the van der Waals parameter variation relative to the van der Waals parameter a associated with the stationary-small-portion yet to be subjected to the deep-stagnation-effect, V is the volume of moving-small-portion 510, a.sub.w is the parameter similar to the van der Waals parameter a, but describing inter-attraction forces between the walls and molecules of the fluid, i.e. the wall-fluid molecular interaction forces; y.sub.w is the distance between moving-small-portion 510 and the walls; and F.sub.skin(u, a+δa, y.sub.w) is a function of u, a+δa, and y.sub.w. If the distance y.sub.w is sufficiently big, the viscosity influence of the walls becomes negligible. The difference (a.sub.w−a−δa) defines the effect of viscosity. When the attractive forces between the walls and molecules of the fluid are stronger than the fluid's inter-molecular forces, i.e. (a.sub.w−a−δa)>0, the fluid's molecules are “sticking” to the walls, and the fluid develops viscous properties causing the wall-fluid molecular interaction forces cumulative action against fluid portion 510's motion direction accompanied by a dissipation of the kinetic energy of fluid portion 510 into the fluid portion 510's heat energy; and when the attractive forces between the walls and molecules of the fluid are weaker than the fluid's inter-molecular forces, i.e. (a.sub.w−a−δa)<0, the walls develop phobic repellent properties. A so-called “free-slip” motion condition, corresponds to the case, when the attractive forces between the walls and molecules of the fluid compensate the fluid's inter-molecular forces, i.e. (a.sub.w−a−δa)=0.

(98) The partial osmotic-like static-pressure P.sub.osmotic defines the osmotic-like effect triggered by the gradients of density and temperature. This can be formalized as
P.sub.osmotic=F.sub.osmotic(a+δa,∇ρ,∇T) Eq. (5.4b),
where F.sub.osmotic(a+δa,∇ρ,∇T) is a function of the van der Waals parameter a allowed to be varied and of the gradients ∇ρ and ∇T. The gradients ∇ρ and ∇T depend on the gradient of the velocity-vector ∇u. If all the gradients equal zero, the osmotic-like effect becomes as the diffusion caused by the Brownian random motion of the fluid's molecules.

(99) So, the partial viscous-static-pressure P.sub.viscous is represented as the sum of two items, namely:
P.sub.viscous=P.sub.skin+P.sub.osmotic Eq. (5.4c).

(100) Considering the general case of fluid portion 510 of FIG. 5b that may move either within or out of the imaginary boundary layer, the cumulative-inner-static-pressure P is interpreted as comprising the mentioned items:
P=P.sub.in+P.sub.z=P.sub.s+P.sub.drag+P.sub.viscous+P.sub.z Eq. (5.4d),
which can be further decomposed as the following:
P=P.sub.s+(δP.sub.a+δP.sub.b+δP.sub.c)+(P.sub.skin+P.sub.osmotic)+P.sub.z Eq. (5.4e)
The characteristic heat portion per unit mass, indicated by Q, stored in fluid moving-small-portion 510's molecular Brownian random motion, related to degrees of freedom causing the fluid molecules cumulative impact defining the inner-static-pressure P.sub.in, equals

(101) 0 $\begin{matrix} Q = RT = \frac{P_{in}}{ρ}, & Eq . (5.4) \end{matrix}$
where T is the fluid moving-small-portion 510 absolute temperature that, in general, differs from the temperature T.sub.s of the stationary case satisfying the stationary equation (5.2e), and the generalized specific fluid constant R is defined for moving-small-portion 510 as R=rR.sub.0/μ, where r=V/(V−b). Combining equations (5.2), (5.3) and (5.4), one can derive that

(102) $\begin{matrix} Q + G = \frac{P}{ρ}, & Eq . (5.5) \end{matrix}$
when an adiabatic case is considered. In a particular case, when the effect of the gravitational influence is negligible, the cumulative-inner-static-pressure P is identical with the inner-static-pressure P.sub.in, and the equation of a moving molecular fluid state is derived from the equation (5.5) as:
P=P.sub.in=ρQ=ρRT, if P.sub.z=0 Eq. (5.5a).
Taking into account equation (5.5), one can rewrite integral equation (5.1) as:

(103) $\begin{matrix} \frac{\partial}{\partial t} \int ρ udV = - \oint_{S} ρ uu .Math. ndS - \oint_{S} ρ (Q + G) ndS . & Eq . (5.6 a) \end{matrix}$
Applying Gauss's theorem to the integrals of the right part, one can specify this as:

(104) $\begin{matrix} \frac{\partial}{\partial t} \int ρ udV = - \int \nabla ρ uudV = - \int \nabla ρ (Q + G) dV, & Eq . (5.6 b) \end{matrix}$
or, in differential form:

(105) $\begin{matrix} \frac{\partial}{\partial t} u = - \nabla (uu) - \nabla (Q + G), & Eq . (5.6) \end{matrix}$
where ∇ is the vector differential operator.

(106) The term “∇Q” of the equation has the sense of a force per mass unit interrelated with a change in fluid thermodynamic state, the term “∇(uu)” has the sense of an inherent convective self-acceleration of fluid portion 510, and the term “∇G” has the sense of a gravitational force.

(107) The momentum conservation equation in form (5.6) is applicable to viscous fluid flow being either almost incompressible as liquid or compressible-expandable as gas. Noticing that the inner-static-pressure, in the general case, equals+P.sub.in P.sub.in=P.sub.s+P.sub.drag+P.sub.viscous, the exact solution of (5.6) for a steady-state flow is the Bernoulli theorem: (P.sub.in/ρ)+(zg)+(u.sup.2/2)=Const that confirms adequateness of equation (5.6).

(108) Mass Conservation or Equation of Continuity

(109) The conservation of mass says that the variation of the mass in a volume must be entirely due to the inflow or outflow of mass through a closed surface S of that volume, namely:

(110) $\begin{matrix} \frac{\partial}{\partial t} \int ρ dV = - \oint_{S} ρ u .Math. ndS . & Eq . (5.7 a) \end{matrix}$
Using Gauss's theorem, one can specify this as:

(111) $\begin{matrix} \frac{\partial}{\partial t} \int ρ dV = - \int \nabla .Math. (ρ u) .Math. dV, & Eq . (5.7 b) \end{matrix}$
and so in differential form:

(112) $\begin{matrix} \frac{\partial}{\partial t} ρ + \nabla .Math. (ρ u) = 0. & Eq . (5.7) \end{matrix}$
The solution of (5.7) for a stationary case can be written as the equation of continuity: Aρu=Const, where A is the fluid flow cross-section area.
Generalized Adiabatic Compressibility Parameter

(113) The mathematical equation for a hypothetical ideal gas undergoing a reversible adiabatic process is
P.sub.idealV.sup.j=Const Eq. (5.8a),
where j is the adiabatic compressibility-constant, defined for the hypothetical ideal gas as j=1+R.sub.0/C.sub.V=1+2/f, where C.sub.V is the specific heat capacity for constant volume, and f is the number of degrees of freedom per molecule of gas wherein f depends on a configuration of the hypothetical ideal gas molecules.

(114) One can spread the logic of the kinetic theory of gas to define a so-called adiabatic compressibility parameter γ, now generalized for a real fluid, specifying factors reducing the degrees of freedom of the fluid's molecules. These are the compression ratio r=V/(V−b) and an involved function ϕ(a) of the van der Waals parameter a+δa. The involved function ϕ(a+δa) has a sense of an influence of the internal inter-molecular potential-energy-per-unit-mass on the degrees of freedom of the fluid's molecules and is expressed as:

(115) $\begin{matrix} ϕ (a + δ a) = \frac{P_{in}}{P_{in} - P_{a} - δ P_{a}} = \frac{ρ RT}{ρ RT - U - δ U} . & Eq . (5.8 b) \end{matrix}$
Therefore, one can define the generalized adiabatic compressibility parameter γ as
γ=1+rϕ(a+δa)R.sub.0/C.sub.V=1+2rϕ(a+δa)/f, i.e. γ=1+rϕ(a+δa)(1−j) Eq. (5.8c),
where j now has the sense of the adiabatic compressibility parameter, defined for the real fluid, but imagined as a hypothetical ideal gas composed of the same molecules in the assumption that the conditions a+δa=0 and b=0 are satisfied and are interrelated to the conditions ϕ(a+δa)=1 and r=1, correspondingly. The condition γ>>1 is satisfied for liquids and ionized gases (i.e. plasma), so the following simplified equation becomes relevant:

(116) $\begin{matrix} {\begin{matrix} γ = j & for hypothetical ideal gases \\ γ = 1 + r (j - 1) & for real gases \\ γ >> 1 & for real liquids and plasma \\ γ .fwdarw. \infty & for hypothetical incompressible liquids \end{matrix} . & Eq . (5.8 d) \end{matrix}$

(117) The definition of the generalized adiabatic compressibility parameter γ allows to derive an equation for the real fluid undergoing a reversible adiabatic process as:
P.sub.inV.sup.γ=Const Eq. (5.8).

(118) In a particular case, when the effect of the gravitational influence is negligible, the cumulative-inner-static-pressure P becomes identical with the inner-static-pressure P.sub.in, and the equation (5.8) for the real fluid undergoing a reversible adiabatic process can be specified as:
PV.sup.γ=P.sub.inV.sup.γ=Const, if P.sub.z=0 Eq. (5.8e).

(119) For a hypothetical ideal gas, the conditions r=1 and ϕ(a)=1 are satisfied, and equations (5.8) and (5.8e) revert to equation (5.8a).

(120) Energy Conservation

(121) The conservation of energy says that the variation of the energy in a volume must be entirely due to the inflow or outflow of energy through a closed surface S of that volume. Energy exists in many forms. In the case, wherein portion 510 is small sufficient to have no whirling groups of molecules, making a complete rotating cycle within portion 510 (i.e. to have no inner turbulent motions), considering a unit mass of fluid portion 510, one can take into account the following forms of the energy: kinetic energy K=u.sup.2/2, defined by cumulative kinetic-energy-per-unit-mass of fluid molecules motion in a prevalent direction; potential gravitational energy G=zg, stored in the unit mass in the gravitational field of the Earth; total heat Q.sub.tot as the cumulative kinetic energy per unit mass stored in a fluid molecular Brownian random motion that for a van der Waals gas is defined as Q.sub.tot=RT×(r(j−1)), where R=rR.sub.0/μ. To define the total internal energy per unit mass, indicated by U.sub.in, the change in degrees of freedom of the fluid's molecules caused because of the internal inter-molecular potential-energy-per-unit-mass U+δU is taken into the consideration via the definition of generalized adiabatic compressibility parameter γ, such that the total internal energy per unit mass, indicated by U.sub.in, is quantified as U.sub.in=Q.sub.tot+U+δU=RT×(γ−1)=Q×(γ−1), wherein the only characteristic heat portion per unit mass Q=RT, stored in a fluid molecular Brownian random motion, is related to degrees of freedom causing the fluid molecules cumulative impact on the boundary surfaces of moving-small-portion 510.
Thereby, the total cumulative energy applicable to the fluid motion is the volume integral of ρ(K+G+Q), and wherein the advection of energy through the control volume surface is the surface integral of ρ(K+G+Q)u.Math.n. Thus, the conservation equation of energy is:

(122) 0 $\begin{matrix} \frac{\partial}{\partial t} \int ρ (K + G + Q) dV = - \oint_{S} ρ (K + G + Q) u .Math. ndS . & Eq . (5.9 a) \end{matrix}$
Using Gauss theorem one gets:

(123) $\begin{matrix} \frac{\partial}{\partial t} \int ρ (K + G + Q) dV = - \int \nabla [ρ (K + G + Q) u] dV . & Eq . (5.9 b) \end{matrix}$
Since this must be valid for all control volumes V, one gets the differential form of the energy conservation equation:

(124) $\begin{matrix} \frac{\partial}{\partial t} ρ (K + G + Q) + \nabla [ρ (K + G + Q) u] = 0, & Eq . (5.9 c) \end{matrix}$
or, substituting the defined expressions for the kinds of energy, it can be written as:

(125) $\begin{matrix} \frac{\partial}{\partial t} ρ (\frac{u^{2}}{2} + zg + RT) = - \nabla [(ρ u) (\frac{u^{2}}{2} + zg + RT)] . & Eq . (5.9) \end{matrix}$
In a stationary case, equation (5.9) can be simplified as:

(126) $\begin{matrix} \nabla [(ρ u) (\frac{u^{2}}{2} + zg + RT)] = 0. & Eq . (5.10 a) \end{matrix}$
Comparing (5.10a) with mass conservation equation (5.7), one can conclude that

(127) $\begin{matrix} \frac{u^{2}}{2} + zg + RT = Const & Eq . (5.10 b) \end{matrix}$
Taking into the account that=RT=P.sub.in/ρ, one obtains the Bernoulli theorem for stationary flow:

(128) $\begin{matrix} \frac{u^{2}}{2} + zg + \frac{P_{in}}{ρ} = Const, & Eq . (5.10) \end{matrix}$
as was predicted.

(129) The set of specified equations (5.2), (5.3), (5.4), (5.5), (5.6), (5.7), (5.8), and (5.9) represents the generalized equations of molecular fluid motion, the adequacy of which is confirmed by the Bernoulli theorem, equation (5.10). A method for computational fluid dynamics comprising the momentum conservation equation (5.6) expressed via the gradient of the characteristic heat portion ∇Q is a subject of the present invention.

(130) In view of the foregoing description with reference to FIG. 5b, it will be evident to a person skilled in the art that, in contrast to the continuum mechanics approach based on the introduction of viscosity constants, the description of the drag and viscosity effects by molecular interactions defined in frames of the kinetic theory of matter is one of the primary principles of the present invention.

(131) In view of the foregoing description with reference to FIG. 5b, it will be evident to a person skilled in the art that the described approach, being adapted to fluid portion 510 moving near real walls of body 511, excludes the d'Alembert paradox formulated in frames of the classical continuum mechanics, because of either repellent or sticking properties of the arisen partial drag-static-pressure P.sub.drag depending on a direction of the motion velocity of fluid portion 510 and the walls' curvatures. This follows also from the kinetic theory of gas, where the term “pressure” is defined as a measure of the random moving molecules' impact effect acting on a wall. So, considering a moving body, for simplicity, having a spherical shape, the relative mean velocity-vector of the impacting molecules random motion depends on the body's velocity value and direction, according to Galilean relativity. Thus, the difference between the impact effects, acting on the forward and rear sides of the moving body, defines the non-zero cumulative partial drag-static-pressure P.sub.drag. Furthermore, considering a moving body, having an airfoil wing-like shape triggering the Coanda-effect, the partial pressure-c δP.sub.c, as a component of the partial drag-static-pressure P.sub.drag, provides a jet-effect and, in a certain condition, triggers the de Laval effect as described below with reference to FIG. 7c as well as with references to FIGS. 8a, 8b, 8c, 8d, 9a, 9b, 9c, 9d, 9e, and 9f.

(132) In view of the foregoing description with reference to FIG. 5b, it will be evident to a person skilled in the art that the partial viscous-static-pressure P.sub.viscous, comprising the partial skin-fiction static-pressure P.sub.skin and osmotic-like static-pressure P.sub.osmotic, depends on the fluid temperature. In particular, for gases, higher temperature results in a dominant increase of the partial osmotic-like static-pressure P.sub.osmotic; and for liquids, higher temperature results in a decrease of the van der Waals parameter a accompanied by the skin-friction static-pressure P.sub.skin decrease, primary defining the partial viscous-static-pressure P.sub.viscous decrease.

(133) In view of the foregoing description with reference to FIG. 5a, it will be evident to a person skilled in the art that, considering a molecular fluid in frames of the van der Waals approach, without loss of generality, one can apply a modification of the van der Waals equation of state for a molecular fluid. It may be either the Redlich—Kwong equation, and/or the Berthelot model, and/or the Dieterici model, and/or the Clausius model, and/or the Vidal equation, and/or the Peng-Robinson equation of state, and/or the Wohl equation, and/or the Beattie-Bridgman model, and/or Benedict-Webb-Rubin equation as well as further generalizing modifications.

(134) In view of the foregoing description with reference to FIGS. 5a and 5b, it will be evident to a person skilled in the art that, applying a certain resolution size of fluid portion 510 to a discrete approximation in the computational fluid dynamics, some whirling groups of molecules, i.e. some turbulent motions of fluid, become hidden within the resolution. In other words, considering a sufficiently large fluid portion 510 as a cell of the discrete approximation in the computational fluid dynamics, the hidden turbulent motion of the groups of molecules, whirling within the fluid portion 510, is interpreted as the molecules Brownian random motion. This means that the temperature of fluid portion 510, involved into equation (5.9), should be understood in a widened sense as a measure proportional to the average molecular kinetic energy of both: the molecules Brownian random motion and the hidden turbulent motion of the whirling groups of molecules.

(135) Waves in Fluid

(136) The acoustic (elastic) wave propagating in a molecular fluid medium is defined as a periodically oscillating motion of a molecular fluid portion relative to a stationary point, wherein the periodically oscillating portion is subjected to an external energetic forced action resulting in the acoustic wave process. The inventor points out that the acoustic wave process is a particular case of the molecular fluid motion in accordance with the set of equations (5.6), (5.7), and (5.9), where the fluid density is given by a periodically oscillating function, wherein the wavenumber is interrelated with the cycle frequency and the velocity of sound. Namely, (t, z)=ρ.sub.0+δρ×cos(ωt−κz), where: ρ.sub.0 is the effective mass density of the fluid matter, δρ is the oscillation amplitude of the mass density of the fluid matter, t is current time, z is distance from a certain spatial point, ω is cycle frequency of the oscillation, and κ is wavenumber of the acoustic wave, associated with the periodically-oscillated mass density, wherein κ=ω/u.sub.sound, where u.sub.sound is velocity of sound in the molecular fluid.

(137) The total internal energy per unit mass U.sub.in, comprises the portion of energy, indicated by δU.sub.in, which is defined as acquired from the external energetic forced steady-state oscillating action. The acquired portion, δU.sub.in, per unit mass is permanently refreshing locally and is traveling along the direction of the acoustic wave propagation such that the total internal energy per unit mass, U.sub.in, remains constant. The inventor points out that the energy traveling (i.e. work) occurs in an adiabatic process, i.e. occurs at the expense of the internal heat energy of the molecular fluid itself. For simplicity, ignore the non-zero partial viscous-static-pressure P.sub.viscous causing the irretrievable dissipation of the acoustic wave energy into the warmth of the molecular fluid medium. The set of equations (5.6), (5.7), and (5.9), in particular, says that the wave process is a process of the energy transformation from one kind of the energy into another kind of the energy. Namely, the kinetic energy of oscillating motion is transforming into the potential energy interrelated with the partial drag-static-pressure P.sub.drag defined by equation (5.3b) as composed of three varying additive components: P.sub.drag=δP.sub.a+δP.sub.b+δP.sub.c and accompanied by a change of the molecular fluid density and temperature and so interrelated with a change of the molecular fluid state in a revertible adiabatic process and, vice versa, the molecular fluid portion potential energy, interrelated with the partial drag-static-pressure P.sub.drag, becomes contributed to the convectively acquired kinetic energy of the oscillating motion. The change in fluid state interrelated with the oscillating motion in an adiabatic process corresponds to a certain change in the internal heat energy of the molecular fluid, namely, ΔQ.sub.a=RΔT.sub.a, where ΔQ.sub.a is the change of characteristic heat portion per unit mass, wherein the value of the adiabatic temperature change ΔT.sub.a=T.sub.2−T.sub.1 is bonded with the varying partial drag-static-pressure P.sub.drag by the relation: T.sub.2/T.sub.1=(P.sub.2/P.sub.1).sup.(γ−1)/γ, where P.sub.1 and P.sub.2 are the partial drag-static-pressures P.sub.drag of the subject fluid portion in two opposite states of the oscillating portion of fluid in the adiabatic process, correspondingly, and γ is the generalized adiabatic compressibility parameter as defined by equation (5.8c), wherein the value γ=7/5 is a good approximation for natural air as consisting dominantly of diatomic molecules.

(138) The inventor points out that the mechanism of the adiabatic transformation between the internal heat energy and the convectively acquired kinetic energy of the oscillating motion is determined by the Coanda-jet-effect quantified by the partial pressure-c δP.sub.c. The adiabatic transformation between the internal heat energy and the convectively acquired kinetic energy of the oscillating motion is in conformance with the set of equations (5.6), (5.7), and (5.9), and so the exact solution for acoustic wave, propagating in a prevalent direction, as a particular case of the molecular fluid steady-state oscillating motion, is the Bernoulli theorem saying that the value (P.sub.in/ρ)+(u.sup.2/2) is constant along the prevalent direction. The inventor points out that the external energy of the forced action: on the one hand, is a source of the wave process; as well as, on the other hand, is a trigger providing for the periodically oscillating mutual transformation of the molecular fluid portions energy between the oscillating motion and the molecular fluid portions internal heat energy defined by the varying partial drag-static-pressure P.sub.drag, wherein the triggered energy transformation occurs adiabatically.

(139) This, in particular, says that the energy, brought by an acoustic wave, is composed of the external energy of the forced action and a positive portion of energy, which is self-extracted from the internal heat energy of the molecular fluid due to the Coanda-jet-effect quantified by the partial pressure-c δP.sub.c. Thus, the inventor points out that the wave process is accompanied by the Coanda-jet-effect, i.e. by a triggered effect of the molecular fluid portions convective self-acceleration, occurring adiabatically at the expense of the internal heat energy of the ambient fluid medium.

(140) For the purposes of the present invention, to emphasize the inherent jet-effect of the propagating acoustic wave, the term “waving jet-effect” should be understood as a kind of the Coanda-jet-effect specified as being applied to inner portions of a molecular fluid, as a tendency of an oscillatory moving-small-portion to be attracted to and aligned with a curvature of a nearby fragment of an imaginary boundary of a neighbor inner portion;

(141) For the purposes of the present invention, to emphasize the jet-effect nature of the acoustic radiation pressure described hereinabove in the BACKGROUND OF THE INVENTION, subparagraph “Radiation Pressure”, the term “radiation jet-effect” should be understood as a kind of jet-effect specified as a tendency of propagating acoustic wave to push an obstacle exposed to the propagating acoustic wave; wherein the tendency, observed as the excessive radiation pressure by the propagating acoustic wave, is interrelated with the tendency of the acoustic wave propagation in a prevalent direction.

(142) The inventor takes note that the terms “radiation jet-effect” and “waving jet-effect” are of interrelated senses. In other words, the inventor interprets the radiation jet-effect as a self-revealing-and-manifestation of the triggered waving jet-effect that, in turn, is a self-revealing-and-manifestation of the triggered Coanda-jet-effect. Further, the inventor points out that, when the external energetic source of an acoustic wave acts as a localized oscillator only, the acoustic wave is characterized by propagation in a prevalent direction, and, if to ignore the acoustic wave dissipation, the acoustic wave propagation, as the wave energy traveling, occurs adiabatically. The inventor takes note the adiabatic character of the acoustic wave propagation allowing for a conveying the acoustic wave energy from the localized external energetic source of the acoustic wave to an acoustic wave detector placed far from the localized external energetic source.

Interference of Acoustic Waves

(143) The principle of superposition of waves states that when two or more propagating waves of the same type inter-join at a point, the resultant amplitude at that point is equal to the vector sum of the amplitudes of the individual waves. If a crest of a wave meets a crest of another wave of the same frequency at the same point, then the amplitude is the sum of the individual amplitudes—this is constructive interference. If a crest of one wave meets a trough of another wave, then the amplitude is equal to the difference in the individual amplitudes—this is known as destructive interference.

(144) The inventor points out that as the acoustic waves are characterized by dominant longitudinal oscillations inherently accompanied by minor cross-sectional oscillations of a molecular fluid portion, i.e. are characterized by a specific field of velocities, then, considering the acoustic waves superposition, one expects the following specific self-revealing-and-manifestations of the interference, namely, when the two in-phase acoustic waves are joining substantially collinear, one expects the origination of the constructive interference; when the two anti-phase acoustic waves are joining substantially collinear, one expects the origination of the destructive interference; when the two identical acoustic waves are joining when propagating in the opposite directions, one expects the origination of a so-called standing wave as a result of the constructive-destructive interference; and when the two acoustic waves (as dominantly longitudinal waves) are meeting when propagating in the inter-perpendicular directions, one expects the origination of a specific kind of interference, for the purposes of the present invention, called an “orthogonal interference”.

In Relation to a Single Wave in a not Disturbed Molecular Fluid

(145) When a portion of fluid is disturbed by the single acoustic wave, propagating in a prevalent direction and characterized by a certain wavelength, the fluid portion is composed of molecules: moving randomly in all the directions with the Brownian distribution of velocities, wherein the mean squared velocity of the Brownian motion of the molecules, equal to u.sub.B1, corresponding to the velocity of the single acoustic wave propagation in the prevalent direction in the case, and, in addition, dominantly-longitudinally oscillating along the prevalent direction, collinear to the wave propagation, with the velocity u oscillating between the minimal value −u.sub.1 and the maximal value +u.sub.1 relative to a stationary point; the density ρ of the portion is oscillating as interrelated with the oscillating velocity in accordance with the equation of continuity; wherein the inner-static-pressure and temperature of the portion are oscillating as well as interrelated with the oscillating density in accordance with the Van der Waals law of the fluid state applied to an adiabatic process; the wave energy U.sub.1 per wavelength, brought by the single acoustic wave, is equal to U.sub.1=0.5ρ.sub.1u.sub.1.sup.2, where ρ.sub.1 is the density of a small sub-portion of the molecular fluid, wherein the small sub-portion having the linear size along the prevalent direction being much lesser than a quarter of the wavelength and moving with the maximal velocity u.sub.1; and the cross-sectional area A of any portion of fluid is oscillating as well, according to the equation of continuity Aρu=Const, i.e. the dominant longitudinal oscillations of a molecular fluid portion are inherently accompanied by cross-sectional oscillations.

In Relation to the Constructive Interference

(146) When a portion of fluid is disturbed by two collinear in-phase acoustic waves, both characterized by the same wavelength, at the first glance, the constructive interference is observed as a seemingly usable energy excess when one uses a classic detector of the usable wave energy, reacting on the fluid molecules oscillating impact, i.e. reacting on the oscillation of locally-excessing pressure; and in a more detailed analysis, seeing that the two in-phase waves are disturbing the fluid portions by oscillations in unison, thereby superposing the fields of velocities and thereby repeatedly reinforcing the waving jet-effect, the resulting oscillation velocity reaches the maximal value u.sub.+ equal to u.sub.+=u.sub.1+u.sub.2, where indexes “1” and “2” correspond to the two in-phase waves propagating separately, and index “+” corresponds to the case when the two in-phase waves join to result in the constructive interference; thereby causing the specifically-asymmetrical redistribution of molecules motions degrees of freedom, the disturbed fluid portion becomes composed by molecules, moving randomly in all the directions with the Brownian distribution of velocities and, in addition, oscillating in the prevalent direction, collinear to the two in-phase waves propagations; wherein the oscillating velocity reaches the maximal value u.sub.+ relative to a stationary point; the relative velocity increase up to u.sub.+=u.sub.1+u.sub.2 is higher than a hypothetic increase of velocity up to √{square root over (u.sub.1.sup.2+u.sub.2.sup.2)}, which would be reached if considered as limited by the cumulative energies brought by the two in-phase waves only; wherein actually, the relative velocity increase up to u.sub.+=u.sub.1+u.sub.2 occurs also at the expense of the internal heat energy and the corresponding established mean squared velocity of the Brownian motion of the molecules equals u.sub.B+, such that the condition u.sub.B+<u.sub.B1 must be satisfied in the case. Corresponding varying partial drag-static-pressure P.sub.drag interrelates with the velocity of oscillation; and the cumulative usable wave energy u.sub.+ per wavelength, brought by the two superposed collinear and in-phase acoustic waves, is equal to U.sub.+=0.5ρ.sub.+u.sub.+.sup.2, where ρ.sub.+ is the density of a small sub-portion of the molecular fluid, wherein the small sub-portion having the linear size along the prevalent direction being much lesser than a quarter of the wavelength and moving with the maximal velocity u.sub.+, i.e. u.sub.+=0.5ρ.sub.+(u.sub.1+u.sub.2).sup.2. For simplicity, ρ.sub.+≈ρ.sub.1≈ρ.sub.2. In the case when u.sub.1=u.sub.2, the cumulative usable wave energy U.sub.+ per wavelength, brought by the two superposed collinear and in-phase acoustic waves, is equal to fourfold usable wave energy U.sub.1 per wavelength, brought by a single wave, i.e. U.sub.+=4U.sub.1.
The inventor points out that the increase of the maximal value u.sub.+ of the oscillating velocity relative to a stationary point occurs at the expense of the mean squared velocity of the Brownian motion of the molecules u.sub.B1 (i.e. u.sub.+<u.sub.B1). This, in particular, explains why, in a thermo-acoustic heat engine, an acoustic resonator plays the role of a “cold sink”, and says that the maximal value u.sub.+ is restricted by the origin mean squared velocity of the Brownian motion u.sub.B1. Looking ahead, in view of the description of subparagraph “Convergent-Divergent Jet-Nozzle” referring to FIG. 6a of the invention, it will become evident to a person studied the present invention that the relative velocity u.sub.+, which can be reached in an adiabatic waving process, is characterized by M-velocity being lower than the specific M-velocity, indicated by M.sub.*, specified in equation (6.9) and, for air, estimated as of about M.sub.*≈0.5345. I.e. the condition u.sub.+<u.sub.B+×M.sub.* must be satisfied. This condition restricts the adiabatic increase of wave power brought by a classic waving acoustic wave, while a shock wave may bring higher power.
For the purposes of the present invention, the term “usable wave energy per wavelength” should be understood as partial wave energy being proportional to the second power of the resulting amplitude of the wave, and hence being detectable by a classic detector of waves, reacting on the resulting amplitude of wave; and the term “enhanced waving jet-effect” should be understood as the waving jet-effect, which is reinforced repeatedly applying constructive interference.

In Relation to the Destructive Interference

(147) When a portion of fluid is disturbed by two collinear anti-phase acoustic waves, both characterized by the same wavelength, and the same amplitude, wherein the oscillating velocities of molecules for each acoustic wave are between ±u.sub.1 and ±u.sub.2, correspondingly, relative to a stationary point and are always contra-directed, i.e. providing the zero cumulative impact, at the first glance, the destructive interference is observed as a seeming energy annihilation when one uses a classic detector of wave energy, reacting on the fluid molecules oscillating impact, i.e. reacting on the oscillation of locally-excess pressure; and in a more detailed analysis, taking note that the principle of superposition, essentially says that any complex motion can be divided into two or more simple ones, the superposition of two fields of the two anti-phase oscillating velocities associated with the two anti-phase acoustic waves, correspondingly, results in a complex field of the oscillating velocities, wherein the complex field of the oscillating velocities hides the two basic fields of the anti-phase oscillating velocities; seeing that the two anti-phase waves are disturbing the fluid portions by oscillations in anti-unison thereby superposing the fields of velocities and thereby causing the specifically-asymmetrical redistribution of molecules motions degrees of freedom: (a) the disturbed fluid portion becomes composed of molecules moving randomly in all the directions with the Brownian distribution of velocities and, in addition, oscillating in the prevalent direction, collinear to the common direction of the two anti-phase waves propagations; wherein the velocities of molecules oscillations are vectored in the opposite directions simultaneously within each small volume having the linear size along the prevalent direction being much lesser than a quarter of the wavelength; (b) the specific asymmetry of such a distribution of velocities with respect to the directions is characterized by hidden relative velocities in the direction of the two anti-phase acoustic waves propagation, wherein the hidden maximal relative velocity of anti-unison oscillating molecules, equals u.sub.−=u.sub.1+u.sub.2, according to Galilean relativity; (c) the hidden relative velocity increase interrelates with the corresponding varying partial drag-static-pressure P.sub.drag and defines the acquired latent energy of the superposed acoustic waves where the latent kinetic energy is periodically transforming into the corresponding latent potential energy stored in the hidden stagnations; wherein the hidden relative velocity increase up to u.sub.−=u.sub.1+u.sub.2 is higher than a hypothetic increase of velocity up to √{square root over (u.sub.1.sup.2+u.sub.2.sup.2)}, which would be reached if considered as limited by the cumulative energies brought by the two anti-phase waves only; wherein actually, the hidden relative velocity increase up to u.sub.−=u.sub.1+u.sub.2 occurs at the expense of the molecular fluid internal heat energy, and the corresponding established mean squared velocity of the Brownian motion of the molecules equals u.sub.B−, wherein the condition u.sub.B−<u.sub.B1 must be satisfied in the case; (d) it is expected that a temperature detector, reacting on the local thermal radiation in a prevalent direction, perpendicular to the common direction of the two anti-phase waves propagations, can be used for the detection of the hidden relatively increased velocity oscillation; (e) it is expected that because the velocities of molecules oscillations being vectored in the opposite directions, the molecules motions suffer added impedance, thus, (e.1) while ignoring the added so-called wave-impedance, the latent cumulative wave energy U.sub.− per wavelength, brought by the two superposed substantially collinear and anti-phase acoustic waves, is equal to U.sub.−=0.5ρ.sub.−u.sub.−.sup.2, where ρ.sub.− is the density of a small sub-portion of the molecular fluid, wherein the small sub-portion having the linear size along the prevalent direction being much lesser than a quarter of the wavelength and comprising the contra-directed oscillating motions with the hidden relative maximal velocity u.sub.−, i.e. U.sub.−=0.5ρ.sub.−(u.sub.1+u.sub.2).sup.2. For simplicity, ρ.sub.−≈ρ.sub.1≈ρ.sub.2. In the case when u.sub.1=u.sub.2, the latent cumulative wave energy U.sub.− per wavelength, brought by the two superposed substantially collinear and anti-phase acoustic waves, is equal fourfold wave energy U.sub.1 per wavelength, brought by a single wave, i.e. U.sub.−=4U.sub.1; and thereby, the latent cumulative wave energy of superposed anti-phase acoustic waves is equal to the cumulative usable wave energy of superposed in-phase acoustic waves, i.e. U.sub.−=U.sub.+=4U.sub.1 and hence, in the both cases, the established mean squared velocities of the Brownian motion of the molecules are equal, i.e. u.sub.B−=u.sub.B+, in the accordance with The Energy Conservation Law; and (e.2) when taking into account the added wave-impedance, that provides for a higher adequateness of the destructive interference modeling, the increased wave-impedance, in turn, causes a partial reflection of the pairs of inter-superposed originally anti-phased waves in the back direction.
For the purposes of the present invention, the term “latent wave energy” should be understood as a form of energy that: is undetectable by a classic detector of acoustic waves, reacting on the fluid molecules oscillating impact, i.e. reacting on the oscillation of locally-excessing dynamic pressure; and is detectable by a thermal detector, reacting on the local thermal radiation, wherein, in the case of the acoustic wave in fluid (as a dominantly longitudinal wave), the thermal radiation is dominant in a prevalent direction, perpendicular to the common direction of the two anti-phase waves propagations.

In Relation to the Constructive-Destructive Interference as Standing Wave

(148) When a portion of fluid is disturbed by two collinearly meeting acoustic waves, both characterized by the same wavelength, and the same amplitude, wherein the oscillating velocities of molecules for each acoustic wave are between ±u.sub.1 relative to a stationary point and are locally contra-directed, providing for a completely hidden oscillating motion with the inter-opposite velocities, and locally co-directed, providing for the resulting oscillating motion wherein the oscillating velocities of molecules for the resulting acoustic wave are between ±2u.sub.1, correspondingly, the constructive-destructive interference is observed as a standing wave comprising an alternation of a seemingly energy annihilation at points, which are frequently called nodes, and a seemingly energy maximal excess at points, which are frequently called anti-nodes.

(149) The inventor points out that, in view of the foregoing description of the constructive and destructive interferences of two substantially collinear acoustic waves, the cumulative wave energy of the two meeting waves is fourfold higher than the wave energy of a single wave, wherein the wave energy is observed as usable in the anti-nodes and becomes latent in the nodes, and wherein the acquired wave energy excess is extracted from the fluid internal heat energy due to the enhanced waving jet-effect and so, is accompanied by the reduced established mean squared velocity of the Brownian motion of the molecules.

In Relation to the Orthogonal Interference

(150) When a portion of fluid is disturbed by two orthogonally meeting acoustic waves, wherein the oscillating velocities of molecules for each acoustic wave are between ±u.sub.1 and ±u.sub.2, correspondingly, relative to a stationary point and always are vectored inter-orthogonally, i.e. providing a specific superposition of velocities oscillation, and so for the orthogonal interference, observed as a complex acoustic wave composed of oscillating molecules having elliptic trajectory with the oscillating velocity of √{square root over (u.sub.1.sup.2+u.sub.2.sup.2)} the cumulative wave energy, indicated by U.sub.0, which is brought by the complex acoustic wave, is specified as U.sub.0=0.5ρ.sub.0(u.sub.1.sup.2+u.sub.2.sup.2), where ρ.sub.0 is the density of a small sub-portion of the molecular fluid (for simplicity, ρ.sub.0≈ρ.sub.1≈ρ.sub.2), wherein the small sub-portion having the linear size being much lesser than a quarter of the wavelength and comprising the orthogonally-directed oscillating motions with the relative velocity √{square root over (u.sub.1.sup.2+u.sub.2.sup.2)}; in the case when u.sub.1=u.sub.2, the cumulative wave energy U.sub.0 per wavelength, brought by the two superposed orthogonally directed acoustic waves, is equal double wave energy U.sub.1 per wavelength, brought by a single wave, i.e. U.sub.0=2U.sub.1.

(151) The inventor points out that the complex acoustic wave is propagating in two orthogonal directions and is characterized by two commensurate oscillations: longitudinal and transversal.

(152) In relation to constructive and destructive interferences, the inventor emphasizes that, in the case of two identical, substantially collinear acoustic waves propagating in a molecular fluid, the constructive interference as well as destructive interference, each resulting in a complex wave bringing the wave energy being fourfold higher than the wave energy of alone acoustic wave, wherein the energetic excess is acquired at the expense of the internal heat energy of the molecular fluid due to the enhanced waving jet-effect, and wherein the latent wave energy of the resulting destructive interference is hidden when one uses a detector, reacting on the fluid molecules oscillating impact, i.e. reacting on the oscillation of locally-excessing pressure.

(153) The inventor further points out that the constructive interference composed of N collinear in-phase acoustic waves, each bringing wave energy U.sub.1, performs the resulting acoustic wave bringing the cumulative usable wave energy U.sub.N, equal to U.sub.N=N.sup.2U.sub.1 (of cause, while the condition u.sub.+<u.sub.B+×M.sub.* is satisfied), wherein the energetic excess of ΔU.sub.N=N(N−1)U.sub.1 is acquired at the expense of the internal heat energy of the molecular fluid due to the enhanced waving jet-effect.

(154) The inventor points out that, according to the reciprocity theorem, if a parent acoustic wave, bringing the usable wave energy U.sub.N per wavelength, is subjected to a splitting thereby forming N coherent daughter acoustic waves, each daughter acoustic wave brings the usable wave energy U.sub.1 per wavelength that is lower than the parent usable wave energy U.sub.N per wavelength by the factor N.sup.2, wherein the lack of the wave energy, equal to ΔU.sub.N=N(N−1)U.sub.1, becomes dissipated in the molecular fluid.

(155) Modelling an acoustic wave propagating in a molecular fluid, wherein the acoustic wave is interpreted as composed of complex motions, including the Brownian motion and the oscillating motion of molecules, and wherein the two kinds of the motion storing the two kinds of energy: internal heat and wave energy, correspondingly, which are inter-transferring due to the waving jet-effect, is one of the primary teachings of the present invention.

(156) Hypothetic Electromagnetic Analogue

(157) In relation to electromagnetic waves, according to Maxwell's equations, the electromagnetic wave energy is defined by the intensity of the oscillating electromagnetic field where the electrical and magnetic fields are oscillating in orthogonal planes and with the 90° phase shift thereby providing constant electromagnetic wave energy along the electromagnetic wave propagation path.

(158) The inventor points out that the mentioned teaching related to acoustic waves, saying that the energy inter-transferring between the acoustic wave and the molecular fluid, is hypothetically applicable to the electromagnetic waves to solve the seemingly confusing paradoxes of the constructive and destructive interference of the electromagnetic waves by assuming that the electromagnetic wave interacts adiabatically with the medium as a part of the universe, which is inherently “filled” by the universe background matter and universe background energy (in particular, comprising the latent energy of “electromagnetic gas”), analogously as the acoustic wave interacts with the molecular fluid.

(159) Seeing the similarity of behaviors: on the one hand, of propagation and interference of acoustic waves, and, on the other hand, of propagation and interference of electromagnetic waves,
for the purposes of the present invention, the terms “waving jet-effect” and “radiation jet-effect”, introduced hereinabove in subparagraph “Waves in Fluid”, further should be understood in a broad sense applicable also to the electromagnetic waves. Namely, in relation to the electromagnetic waves: the term “waving jet-effect” or “electromagnetic waving jet-effect” should be understood as a kind of the electromagnetic jet-effect specified as a tendency of an electric field to be attracted to and aligned with a nearby surface interacting with the electric field, wherein the mentioned nearby surface is either a real conductive wall and/or an imaginary wall formed by force-lines of the electric field itself (i.e. it includes the interaction between nearby portions of an oscillating electric field); and the term “radiation jet-effect” should be understood as a well-known phenomenon of electromagnetic radiation pressure, defined in Maxwell's theory by the Poynting vector and observed as “pushing” a conductive obstacle exposed to the propagating electromagnetic wave, as described hereinabove in subparagraph “Radiation Pressure”,
wherein the waving jet-effect and the radiation jet-effect, both occur in an adiabatic process accompanied by the energy inter-conversion between the electromagnetic wave and the universe background energy.

(160) For the purposes of the present invention, the term “latent electromagnetic wave energy” or “latent electromagnetic radiation energy” should be understood as a form of the electromagnetic energy that: is undetectable by a classic detector of electromagnetic radiation, reacting on the electric field oscillation, i.e. reacting on the oscillation of locally-excessing electric and/or magnetic field, and; is detectable by a thermal detector, reacting on the local thermal radiation, i.e. reacting on the latent electromagnetic radiation which, when penetrating into a dense molecular body, becomes perceptual as warmth.

(161) The inventor notes that, while the thermal radiation is a measure of the energetic aspect of the latent electromagnetic wave, it is self-suggested the conjecture that the perception as the aroma is specified by the spectral aspect of the latent radiation.

(162) In view of the foregoing understanding of the theoretical aspect of the molecular fluid motion, as headway as well as oscillating, hereinafter, several exemplary embodiments, constructed in accordance with the principles of the present invention and drown quintessentially-schematically, are given for illustrative purposes only and are not meant to be limiting, wherein the logic of applications using acoustic waves is applicable to applications using electromagnetic waves.

Jet-Effect Embodiments

(163) Fluid-Repellent Structured Surface

(164) For the purposes of the present patent application, the term “corpus”, specified as a space-portion, bordered by a closed solid shell contacting with ambient fluid, should be understood as a configurational aspect of a body submerged in the fluid.

(165) For the purposes of the present patent application, the introduced term “fluid-repellent” should be understood in a wide sense as a property of a material to repel the fluid.

(166) In particular, a fluid-repellent material is either: hydrophobic, i.e. water-repellent; or oleophobic, i.e. oil-repellent; or so-called “omniphobic”, i.e. repelling all known liquids such as water-based, oil-based, and alcohol-based [in particular, a hotter surface is omniphobic]; or ion-repellent, i.e. having a charged surface repulsing an ionized gas or liquid.

(167) The inventor points out that the term “fluid-repellent” assumes a diversity of mechanisms providing the phenomenon of hydrophobicity, for examples: the liquid water is diamagnetic, and so a magnet, for instance, a permanent magnet, is interpreted as hydrophobic; the phenomenon of the Archimedes extrusive force pushing up a body floating on the surface of liquid water is interpreted as a kind of hydrophobicity having gravitational nature; and a body rotating around an own axis of rotation, for instance, a cylinder rotating around its axis of symmetry, results in centrifugal forces at its rotating surface, and so the rotating surface is interpreted as omniphobic.

(168) In view of the foregoing description with reference to FIG. 5b, it will be evident to a person skilled in the art that the partial skin-friction static-pressure P.sub.skin and, hence, the partial viscous-static-pressure P.sub.viscous can be controlled by choosing the body walls' material and constructing the walls porosity, sponginess, and structure providing a reduced difference (a.sub.w−a−δa). For example, a bird's body is covered by fibrous feathers and fuzz. The fibrous feathers and fuzz, making an outer surface layer constructed substantially from the air, provide that, on the one hand, the fibrous structure improves an airflow streamlining and, on the other hand, the outer surface layer has the effective parameter a.sub.w close to the van der Waals parameter a of air (normally, the air is associated with the condition for ideal gas a+δa=0). The minimized difference (a.sub.w−a−δa) minimizes the viscosity effect of an imaginary boundary layer, and therefore, an improved aerodynamic property of the bird's body is expected. Furthermore, the feathers and fuzz are hydrophobic, thereby preventing the porosity from filling by water condensed from the natural humid air. Thereby, to weaken an undesired skin-friction effect, one can use a natural or artificial hydrophobic material, having a fibrous and porous structure comprising many small concavities similar to feathers and fuzz or sponge, covering a surface, contacting with humid airflow. Another example is that the greased feathers of a duck are water-repellent, i.e. hydrophobic, providing a free-slip condition for swimming.

(169) FIG. 5c is a schematic illustration of yet another example of a constructive solution, hypothetically interpreted in accordance with the principles of the present invention, providing compensation of skin-friction resistance. A squama surface fragment 521 of fish 520 is shown also as an enlarged sectional view 522. Fish 520's skin 523 secretes hydrophobic mucus 524 retained by fish-scales 525, having a sectional profile of curved cogs. First, hydrophobic mucus 524 covers the surfaces of fish-scales 525, forming a hydrophobic outer layer as an inherent attribute of the fish body 520's hydrodynamic-surface, wherein the condition (a.sub.w−a−δa)<0 provides for a free-slip motion. Moreover, protruding fish-scales 525 are configured and arranged such that hydrophobic mucus 524 repels a surrounding water portions 5271, 5272, 5273, and 5274 with repulsive forces 5281, 5282, 5283, and 5284, correspondingly, wherein repulsive forces 5281, 5282, 5283, and 5284 act cumulatively in unison along an airfoil orientation providing for a “negative drag”. This cumulative action, dominantly, in the backward downstream direction provides a repulsing tendency as a kind of jet-effect.

(170) For the purposes of the present patent application, the terms “phobic-repulsing jet-effect”, “fluid-repellent jet-effect”, and, in particular, the term “hydrophobic jet-effect” should be understood as the described kind of jet-effect. A parabolic profile of mucus 524's surface fragment 526 provides for an enhanced hydrophobic jet-effect. Thus, both the hydrophobic outer layer and the scaly structure provide the improved hydrodynamic property of fish 520's body.

(171) Reference is now made to FIG. 5d, showing schematically a sectional view of a shaped wall 530, without loss of generality, oriented horizontally. Shaped wall 530 comprises a relief-structured outer layer 531, contacting with ambient water 532. Layer 531, made from a hydrophobic material, has a form of a bar with a series of teeth-like sharp and asymmetrical protrusions, thereby constituting a saw-like relief.

(172) In view of the foregoing description with reference to FIG. 5c, it will be evident to a person skilled in the art that relief-structured outer layer 531 repels adjacent portions 5371, 5372, and 5373 of surrounding water 532 with forces 5381, 5382, and 5383 correspondingly, wherein forces 5381, 5382, and 5383 are directed dominantly horizontally. This provides a hydrophobic jet-effect that can be useful for motion in the water surrounding. In the case, wherein wall 530 is stationary, the motion of nearby portions 5371, 5372, and 5373 in the prevalent direction [in the case, dominantly horizontal], arises at the expense of the repulsing interactions between the hydrophobic material and the adjacent water portions. This means that, in the final analysis, the water portions motion in the prevalent direction occurs at the expense of the internal heat energy [warmth] of the nearby water portions.

(173) In practice, a shape of relief-structured outer layer 531, contacting with surrounding water and having an asymmetrically saw-like configured relief, can be used for transportation of water portions 5371, 5372, and 5373 along the asymmetrically saw-like configured relief, for example, the water transportation along relief-structured inner walls within a capillary tube, where originating a useful hydrophobic jet-effect in addition to so-called “capillarity effect”.

(174) FIG. 5e is a schematic illustration of a transparent-like body having convex-concave corpus 512. Convex-concave corpus 512 has a rounded airfoil outer convex side, and concave side 514, both contacting with ambient fluid 517. A multiplicity of holes [three shown] 513.1, 513.2, and 513.3 links together both: outside portions 517.1 of the ambient fluid 517 and the ambient fluid 517's portions 517.2 contacting with concave side 514. The concavity of side 514 has a parabolic profile with focal point 516. Focal point 516 comprises a heating element [not shown here], powered at the expense of either burned fuel or electricity. Thereby, hotter focal point 516 becomes omniphobic, repelling nearby ambient fluid portions 517.2 by omniphobic-repulsive van der Waals forces. The ambient fluid molecules, subjected to the omniphobic-repulsive van der Waals forces action, acquire a prevalent component of motion directed radially from the heating element at focal point 516 toward concave parabolic side 514. When concave parabolic side 514 reflects the prevalent radial component of the molecular motion, the molecular prevalent motion component becomes collimated collinearly with sagittal axis 519, thereby forming oufflowing jetstream 518. The headway motion of oufflowing jetstream 518 provides for a jet-thrust. Furthermore, preferably, concave side 514 has outer layer 515 contacting with ambient fluid 517.2. The layer 515 is either heated and/or implemented from a fluid-repellent material. The parabolic profile 514 of fluid-repellent outer layer 515, further acting on the fluid molecules by phobic-repulsive van der Waals forces, partially converts the Brownian random component of the fluid molecular motion into a motion of the molecules in a prevalent direction toward sagittal axis 519, thereby, focusing [i.e. converging] and more accelerating outflowing jetstream 518, in addition to the aforementioned motion collimation.

(175) In particular, it will be evident to a person skilled in the art that the body having convex-concave corpus 512, supplied with a heating element arranged at focal point 516, when submerged in water 517, operates as a motionless hydrophobic-engine or hydrophobic jet-gear or heating-jet engine (having a heating compressor), providing a jet-thrust, wherein one can control the jet-thrust by the heating intensity. A net-efficiency of such a hydrophobic-engine, having a configured convex-concave corpus 512, is defined by the ratio of power consumed by the heating element to the useful kinetic power of outflowing jetstream 518 headway motion. The net-efficiency may come close to 100% if a dominant headway motion of outflowing jetstream 518 is obtained by convex-concave corpus 512 shape optimization. Moreover, water portions 517.2, yet to be accumulated into outflowing jetstream 518, are also subjected to a hydrophobic jet-effect, originated by parabolic fluid-repellent layer 515, resulting in an increase of the outflowing jetstream 518 headway motion kinetic power at the expense of the water warms and thereby, in principle, allowing for the net-efficiency to become even higher than 100%. Furthermore, outflowing jetstream 518 can be further subjected to convergence by a convergent funnel [not shown here], and thereby, become further accelerated and cooled. Thus, again, the net efficiency can exceed 100% at the expense of the water warmth.

(176) FIG. 5f is a schematic isometry of a body 540 having a wheel-gear-like configured corpus with overall shape, having a sectional profile similar to a circle-saw, constructed in accordance with an exemplary embodiment of the present invention. Body 540 is submerged in a fluid. The configured corpus of body 540 comprises asymmetrical teeth or teeth-like fins having concave sides, which have outer layers 541, 542, 543, 544, 545, 546, 547 and 548, made from a fluid-repellent material. For simplicity, the fluid is water, and the material is hydrophobic. The hydrophobic sides 541, 542, 543, 544, 545, 546, 547 and 548 of teeth repel the water portions 551, 552, 553, 554, 555, 556, 557 and 558 with phobic-repulsive van der Waals forces 561, 562, 563, 564, 565, 566, 567 and 568 correspondingly, wherein phobic-repulsive van der Waals forces 561, 562, 563, 564, 565, 566, 567 and 568 are directed clockwise, along a substantially-airfoil orientation of wheel-gear-like configured corpus 540. If a hydrophobicity of the teeth sides' material is sufficiently strong, a phobic-repulsing jet-effect, caused by phobic-repulsive van der Waals forces repelling the fluid portions, is observed. The phobic-repulsing jet-effect provides a self-rotation of body 540 in the water surrounding in the inverse-clockwise direction 549 at the expense of the ambient water warmth. Thus, configured corpus 540 provides a hydrophobic jet-effect, accompanied by cooling of the ambient water. Moreover, if the effective diameter 5401 of wheel-gear-like configured corpus 540 is big sufficient, the momentum of the rotating forces becomes perceptible, according to the Archimedes' theory of lever.

(177) For the purposes of the present patent application, the term “fluid-repellent jet-gear”, having a widened sense, is introduced as relating to a body submerged in a fluid, wherein the body corpus has an asymmetrically configured relief having an airfoil orientation and a layer contacting with the ambient fluid, wherein the layer is either made from a fluid-repellent material and/or comprising a heating element making the layer omniphobic, and wherein the configured relief of the “fluid-repellent jet-gear” corpus comprises asymmetrical protrusions, for example, teeth-like fins, or humps, or screwed blades, or convex-concave elements. The asymmetrical corpus is oriented such that the protrusions' fluid-repellent sides repel the fluid portions in a prevalent direction along the corpus airfoil orientation. In a particular case, the fluid is water, the fluid-repellent material is hydrophobic, and the term “hydrophobic jet-gear” or “hydrophobic-engine” is used.

(178) In view of the foregoing description with reference to FIGS. 5c, 5d, 5e, and 5f, it will be evident to a person skilled in the art that the described specifically constructed outer layer of a fluid-repellent jet-gear corpus, contacting with the ambient fluid, is characterized by the following principal features: the outer layer comprises at least one fragment, being fluid-repellent, and that the fluid-repellent fragment's shape is asymmetrical relative to the direction of fluid motion, such that the fluid-repellent fragment repels the fluid portions in a prevalent direction along an airfoil orientation of the corpus. In the case wherein the prevalent direction is dominantly the same as the direction of the fluid motion, such a constructive solution compensates a skin-friction resistance. As well, it will be evident to a person skilled in the art that the described phobic-repulsing jet-effect is more powerful, if either the repulsive forces of the fluid-repellent material are stronger, and/or the fluid-repellent fragments of the fluid-repellent jet-gear's outer layer occupy a bigger area contacting with the ambient fluid, and/or the fluid-repellent fragment shapes are optimized to enhance the prevalent directivity of the phobic repelling. Thereby, constructive solutions, providing developed surface of fluid-repellent fragments resulting in an increased phobic-repulsing jet-effect, can provide that the increased phobic-repulsing jet-effect becomes stronger than a skin-friction resistance effect and, thereby, enables the fluid-repellent jet-gear motion at the expense of the nearby surrounding fluid matter warmth only, i.e. in an adiabatic process, the fluid portions, adjacent to the fluid-repellent jet-gear, become colder than the fluid portions, yet to be subjected to the phobic-repulsing jet-effect.

(179) In view of the foregoing description with reference to FIG. 5f, it will be evident to a person skilled in the art that: a so-called Peltier-element can be adapted to operate as a thermoelectric generator producing electricity at the expense of the temperature difference between water portions subjected and not-subjected to the described hydrophobic jet-effect; and if the ambient fluid is plasma, i.e. an ionized gas or liquid, then an electrically charged surface, repulsing ions of the ionized fluid by electrostatic forces, functions as a fluid-repellent material. In another example, a surface, being hotter than ambient fluid, functions as a fluid-repellent material.

(180) FIG. 5g is a schematic top view of an exemplary aggregation 5600 comprising a set of many hydrophobic jet-gears submerged in water. The hydrophobic jet-gears, similar to body 540, described hereinbefore with reference to FIG. 5f, arranged in-lines and in-columns, without loss of generality, in a horizontal plane. In a more general case, also, aggregation 5600 comprises several such horizontal layers, one above the other, that are not shown here. Aggregation 5600, occupying length 5601 and width 5602, for simplicity, each equal to L, and height, equal to H and comprising several horizontal layers. Dashed curves 5603 symbolize that a number of the lines and columns is substantially greater than shown. A fragment of aggregation 5600 is shown also as an enlarged view 560, where neighbor opposite hydrophobic jet-gears 5610 and 5620 differ in directivity of corpuses' overall airfoil orientation and, in particular, in directivity of asymmetrical teeth having hydrophobic outer layers 5613 and 5623 correspondingly. Hydrophobic jet-gears 5610 repel water portions 5614 with forces 5615, directed clockwise, and hydrophobic jet-gears 5620 repel water portions 5624 with forces 5625, directed inverse-clockwise. Thereby, the neighbor opposite hydrophobic jet-gears 5610 and 5620 repel adjacent portions of surrounding water in unison. Aggregation 5600, comprising the multiplicity of relatively small hydrophobic jet-gears 5610 and 5620, provides an increased cumulative area of hydrophobic outer layers 5613 and 5623 contacting with water. Thereby, the hydrophobic jet-gears 5610 and 5620 of aggregation 5600 are subjected to a cumulative phobic-repulsing jet-effect that can be estimated for the exemplary arrangement as the following. An exemplary hydrophobicity of a hydrophobic material is characterized by a hydrophobic pressure of P.sub.h=0.5 Pa. Imaging a practically implementable hydrophobic jet-gears 5610 and 5620 having an effective diameter of D=1 cm, and comprising 8 teeth, each of gap 5604 d=1.25 mm, and thickness 5605 equal to h=2 mm, one estimates that the hydrophobic-repulsive force per one hydrophobic jet-gear 5610 or 5620 equals F.sub.h=P.sub.h×8×d×h=0.5×8×1.25×10.sup.−3×2×10.sup.−3=10.sup.−5N. On the other hand, one defines the fluid resistance force, indicated by F.sub.drag*, in the frames of continuum mechanics as F.sub.drag*=(6πη×r)u.sub.t, where r is so-called Stokes's radius, u.sub.t is the velocity of a body relative to the considered viscous fluid, and η is the dynamic viscosity of fluid. The dynamic viscosity of water at 20° C. is approximately of η=10.sup.−3 Pa×sec. In the case of rotating hydrophobic jet-gears 5610 and 5620, the value r is estimated approximately, as r≈h/2, thus, the fluid resistance force F.sub.drag* per one hydrophobic jet-gear 5610 or 5620 is estimated as F.sub.drag*≈2×10.sup.−5u.sub.t, wherein the velocity u.sub.t means the effective tangential velocity of rotating teeth 5613 and 5623. The condition F.sub.h=F.sub.drag* defines the reachable effective tangential velocity u.sub.t for the case of no-loaded rotation. So, the hydrophobic-repulsive force F.sub.h=10.sup.−5N can provide a relatively fast no-load rotation of hydrophobic jet-gears 5610 and 5620 corresponding to the effective tangential velocity of teeth 5613 and 5623, equal to u.sub.t=F.sub.h/(2×10.sup.−5)≈0.5 m/sec.

(181) Consider an electricity generator producing useful electricity from the surrounding water warmth, wherein either a subset, composed of hydrophobic jet-gears 5610, and/or a subset, composed of hydrophobic jet-gears 5620, powers a rotor of the electricity generator. If the rotation of hydrophobic jet-gears 5610 and/or 5620 is loaded by the electricity generator resulting in the loaded rotation corresponding to the effective tangential velocity of teeth 5613 and/or 5623 equal to u.sub.h=0.1 m/sec, then the rotation power W.sub.h, produced by the hydrophobic-repulsive force F.sub.h, is of about W.sub.h=(F.sub.h−F.sub.drag*)×u.sub.h≈10.sup.−6W.

(182) A parallelepiped having the horizontal area L×L of 32×32=1000 m.sup.2, and the vertical height of H=1000×h=2 m, can comprise about n=10.sup.10 hydrophobic jet-gears 5610 and 5620 producing the cumulative hydrophobic power of about n×W.sub.h=10 kW. Thereby, such an aggregation occupying a volume of 2000 m.sup.3 can produce an industrial amount of electricity from permanently refreshed warm water. Furthermore, taking into account that the heat of fusion coefficient for water is 335 kJ/kg, the cumulative hydrophobic power of 10 kW, when reduced from water warmth in favor of electric power, at the same time, allows for crystallization of ice from seawater (i.e. allows for operation as an ice-maker) and thereby enables harvesting of desalinated water, wherein providing an industrial amount of potable water of about 100 kg/hour.

(183) In view of the foregoing description with reference to FIG. 5g, it will be evident to a person skilled in the art that: a hydrophobic surface submerged in water operates as a cooler (analogously as the “cold sink” in the aforementioned example with the Beverley Clock described hereinabove in subparagraph “Phenomenon of Hydrophobicity and the Beverley Clock” with the reference to FIG. 1m); one could implement an electricity generator comprising an aggregation of fluid-repellent jet-gears and Peltier-elements operating as thermoelectric generators producing electricity at the expense of the temperature differences caused by the phobic-repulsing jet-effect; and an electricity generator, turbo-electric or thermoelectric, comprising an aggregation of hydrophobic jet-gears could operate efficiently if the surrounding warm water is permanently either refreshed and/or consuming caloric; as well, aggregation 5600 of equidistantly arranged hydrophobic jet-gears, provides for constructive interference of many in-phase superposed acoustic waves.

(184) FIG. 5h is a schematic isometry of a fluid-repellent propeller 570 submerged in the fluid. For simplicity and without loss of generality, describe fluid-repellent propeller 570 submerged in the fluid as hydrophobic-propeller 570 submerged in water surroundings. Hydrophobic-propeller 570 has asymmetrically screwed and oriented airfoil blades 571. For simplicity, consider a case, when asymmetrical airfoil blades 571 forcedly remain stationary. One of the primary features of hydrophobic-propeller 570 is that asymmetrically screwed and oriented airfoil blades 571, constructed in accordance with an exemplary embodiment of the present invention, have at least one side, without loss of generality, frontal side 573, having a layer, made from a strongly-hydrophobic material. As described hereinabove referring to FIGS. 5c, 5d, and 5f, this feature triggers a hydrophobic jet-effect and, thereby, originates a motion of the water sub-portions forming sub-streams 575 having the motion headway component, co-directed with sagittal axis 574, and a whirling component, caused by airfoil blades 571 asymmetries. To reduce distortions and micro-turbulences of sub-streams 575, another side of asymmetrical airfoil blades 571, hidden in FIG. 5h, is made from a weakly-hydrophobic material and/or has a fibrous and porous layer, making the layer as composed of micro-portions of water held in the pores, thereby, minimizing the difference (a.sub.w−a−δa) and, hence, reducing the skin-friction resistance. Assuming an exemplary hydrophobicity of the strongly-hydrophobic material, characterized by a hydrophobic pressure of P.sub.hp=0.5 Pa, and considering an implementable small size of hydrophobic-propeller 570, namely, the effective diameter D.sub.hp=1 cm, one can estimate approximately that: on the one hand, the hydrophobic-repulsive force per one hydrophobic-propeller 570, indicated by F.sub.hp, equals F.sub.hp=P.sub.hp×0.25m×D.sub.hp.sup.2=1.25 π×10.sup.−5N; and on the other hand, the fluid resistance force per one hydrophobic-propeller 570, indicated by F.sub.drag**, is estimated in frames of the classical hydrodynamics as F.sub.drag**=(6πη×r.sub.hp)u.sub.hp, where r.sub.hp is so-called Stokes's radius, chosen for the case as r.sub.hp=D.sub.hp/2, u.sub.hp is the effective local tangential velocity of sub-streams 575 relative to blades 571, and n is the dynamic viscosity of fluid. The dynamic viscosity of water at 20° C. is approximately of n=10.sup.−3 Pa×sec.
The condition F.sub.hp=F.sub.drag** defines the reachable effective velocity u.sub.hp. So, the hydrophobic-repulsive force F.sub.hp can provide a relatively fast motion of sub-streams 575 with the effective local tangential velocity u.sub.hp, equal to u.sub.hp=F.sub.hp/(6πη×r.sub.hp)≈0.42 m/sec. One can translate the effective local tangential velocity u.sub.hp, into the effective velocity u.sub.574 of sub-streams 575 headway motion along sagittal axis 574. The translation depends on the effective angle β.sub.hp of asymmetrically screwed and oriented blades 571 slope relative to sagittal axis 574. The interrelation is u.sub.574=u.sub.hp Cos(β.sub.hp). For instance, u.sub.574≈5 cm/sec for β.sub.hp=83°. The headway motion velocity u.sub.574 defines the hydrophobic headway repelling power per one small hydrophobic-propeller 570 as W.sub.hp=F.sub.hpu.sub.574, estimated approximately as W.sub.hp≈2×10.sup.−4 W.

(185) In view of the foregoing description with reference to FIG. 5h, it will be evident to a person skilled in the art that: the hydrophobic pressure pushes a water portion, which further is subjected to elastic reaction by the ambient water, and so, in addition to the directional jet-thrust, the action generates also a peculiar shock-like acoustic wave propagating in the water medium and being characterized by a peculiar frequency and peculiar wavelength. In particular, an acoustic wave having a chiral circumferential polarization is expected in the case, and hydrophobic-propeller 570 can be interpreted as a source of the peculiar shock-like acoustic wave; and the described logic, applied to hydrophobic-propeller 570 submerged in water and thereby launching water sub-streams 575, is applicable to a propeller, similar to hydrophobic-propeller 570, but having frontal surfaces 573 comprising an outer layer, being electrically charged instead of hydrophobic, and being submerged in an ionized gas, and thereby functioning making sub-streams 575 of the ionized gas.

(186) FIG. 5i is a schematic illustration of a stationary spiral 576 submerged in a fluid. Spiral 576 has helically coiled elaborated airfoil-profiled walls, constructed in accordance with an exemplary embodiment of the present invention. The outer surface 577 of spiral 576, is covered by a fluid-repellent material. Without loss of generality, the fluid is water and the material, covering outer surface 577, is hydrophobic, and so, spiral 576 is hydrophobic as well. Such a configuration, acting on the water surroundings by phobic-repulsive van der Waals forces, creates a helically outflowing water jetstream 578, i.e. having two components of motion, namely: headway along sagittal axis 579 and whirling. The motion occurs at the expense of the internal heat energy of water. The stationary hydrophobic spiral 576 can be interpreted as a hydrophobic-engine lunching jetstream 578.

(187) Exemplary implementation of Constructive Interference

(188) The inventor points out that each ring of spiral 576 acts as a source of a peculiar shock-like acoustic wave, while each pair of the neighbor rings acts as a source of a forced elemental acoustic wave. Furthermore, the sequential in-line arranged pairs of the neighbor rings of spiral 576, acting as an array of sources, generating a multiplicity of the forced elemental acoustic waves, which form a spatial interference with respect to the system of coordinates linked to moving flow 578. Wherein, when, in general, a varying pitch of spiral 576 is especially adapted to the acceleration of water portions, the multiplicity of the forced elemental acoustic waves provides constructive interference where all the forced elemental acoustic waves become superposed in-phase along axis 579. For the sake of clarity, there are N rings in spiral 576 originating N forced elemental acoustic waves, correspondingly. The resulting acoustic wave, formed by the superposition of the N forced in-phase elemental acoustic waves, brings the resulting wave power proportional to the second power of the resulting wave amplitude. Hence, the cumulative usable wave power of the resulting acoustic wave is higher than the sum of powers of the elemental acoustic waves by the factor of N.sup.2, wherein the self-acquired portion of the resulting wave power is self-extracted from the internal heat energy of the ambient water due to the multi-stage repeated waving jet-effect as described hereinabove in subparagraph “Interference of Acoustic Waves”.

(189) It will be evident to a person skilled in the art that a long screw, similar to stationary hydrophobic spiral 576, can be interpreted as a hydrophobic-oscillator launching acoustic beam 578. As well, the mentioned aggregation 5600 (FIG. 5g) of equidistantly arranged hydrophobic jet-gears, provides for constructive interference of many in-phase superposed acoustic waves.

(190) The inventor points out to the legendary story about Tesla's mechanical oscillator, claimed extra-powerful acoustic wave generation of which becomes believable in view of the foregoing description. In contrast to the resonance scheme by Tesla, the proposed superposition of N in-phase acoustic waves (wherein N is a specified number), to provide for the desired constructive interference bringing usable wave power, is easily controllable.

(191) It will be evident to a person skilled in the art that the long screw supplied with an acoustic wave power detector as a power converter is capable of operating as an electricity generator producing electricity from the water warmth due to the hydrophobic jet-effect and the enhanced waving jet-effect.

(192) In view of the foregoing description with reference to FIGS. 5c, 5d, 5f, 5g, 5h, and 5i, it will be evident to a person skilled in the art that: hydrophobic-propeller 570 and hydrophobic spiral 576 can be interpreted as kinds of a fluid-repellent jet-gear, where asymmetrically screwed and oriented airfoil blades are used instead of primitive teeth-like fins; and one can implement fluid-repellent jet-gears of various configurations, for example, having an overall shape in a form of either a saw, or a circle-saw, or a spiral staircase, or a propeller, or a screw of Archimedes.
Rational Explanation of Origin of Life

(193) In view of the foregoing description with reference to FIG. 5i, where an asymmetrical spiral, having a form of the Archimedean screw and having a hydrophobic surface, originates a helical motion of fluid, one expects that, contrariwise, if the asymmetrical spiral, having a hydrophobic surface, is decomposed into many separate chiral particles having a hydrophobic side and being submerged in water, where being arranged and oriented randomly, like a suspended matter, then the water, forcedly and certainly helically-flowing around the separate chiral particles, has a predominance to organize the chiral particles into the mentioned asymmetrical spiral in the form of the Archimedean screw, while other particles, geometries of which are not in a conformance with the water motion, remain not organized into a spiral. Thus, in accordance with the principles of the present invention, a mechanism, providing a regularized aggregation of separate left-handed stereoisomers of amino acids into a coiled sequence thereby forming a ribonucleic acid (RNA) molecule, hypothetically, can be specified and implemented artificially. Furthermore, a certain, forced spatial distribution of water flow velocities can provide for that right-handed stereoisomers of amino acids become aggregated in an orderly manner into a nonexistent inversely-screwed right-chiral molecule, which is mirror-symmetrical to a natural RNA.

(194) Reference is now made to FIG. 5j, a schematic illustration of a pair of hydrophobic-propellers: 570 and 580. Hydrophobic-propeller 570 is the same as shown and described hereinabove referring to FIG. 5h. All reference numerals 571, 573, 574, and 575 are the same as described referring to FIG. 5h. Hydrophobic-propeller 580 has stationary airfoil blades 581, asymmetrically screwed and oriented relative to sagittal axis 584. An imaginary compound of blades 571 and sagittal axis 574 is mirror-symmetrical to an imaginary compound of blades 581 and sagittal axis 584. The chiral compounds are arranged sequentially such that sagittal axes 574 and 584 are collinear. Analogous to the case of blades 571, frontal side 583 of blades 581 is covered with a layer, made from a strongly-hydrophobic material; while, to reduce distortions and micro-turbulences of sub-streams 585, another side of asymmetrical airfoil blades 581, hidden in FIG. 5h, is made from a weakly-hydrophobic material and/or has a fibrous and porous layer, making the layer, contacting with ambient water, as composed of micro-portions of water held in the pores, thereby, minimizing the difference (a.sub.w−a−δa) and, hence, reducing the skin-friction resistance. Airfoil blades 581, triggering the hydrophobic jet-effect, accelerate the water sub-portions forming sub-streams 585 having the motion headway component, co-directed with sagittal axis 584, and a whirling component. As asymmetrical blades 571 and 581 are mirror-symmetrical, the whirls of sub-portions 575 and 585 are in mutually-opposite directions; and as sub-streams 585 are the downstream-continuations of sub-streams 575, the whirls of sub-streams 575 and 585 become mutually-suppressed. Thus, the chiral compounds, being mutually complemental and pushing water forward, create resulting jetstream 588, having dominant headway motion originated by the blades frontal sides hydrophobicity and at the expense of the water warmth. The pair of chiral hydrophobic-propellers 570 and 580 can be considered as a whole and be interpreted as hydrophobic-device 590 lunching jetstream 588. Wherein the power, indicated by W.sub.588, of jetstream 588, launched by small hydrophobic-device 590, having the effective diameter D=1 cm, is higher than 2W.sub.hp, because the mutually-suppressed and therefore reduced power of sub-streams 575 and 585 whirls is at least partially transformed into the power of jetstream 588 headway motion.

(195) The inventor points out that the pair of chiral hydrophobic-propellers: 570 and 580 generates a forced elemental acoustic wave with the wavelength equal to the distance between the chiral hydrophobic-propellers: 570 and 580 along sagittal axis 574. It will be evident to a person skilled in the art that a multiplicity of in-line cascaded pairs of chiral hydrophobic-propellers: 570 and 580 causes as an accelerated jetstream as well as interference of the forced elemental acoustic waves, and using an adapted pitch between and within the pairs, a controlled interference: either constructive and/or destructive, becomes applicable.

(196) FIG. 5k is a schematic illustration of a stationary pair of unbroken chiral spirals having shapes of the Archimedean screws, briefly, screws 592 and 593 having helically coiled airfoil-profiled walls, constructed in accordance with an exemplary embodiment of the present invention. Screws 592 and 593 have a common sagittal axis 594 and differ in direction of coiling: clockwise and inverse-clockwise from a frontal point of view. Chiral screws 592 and 593 are submerged in a fluid. The outer surfaces 596 and 597 of chiral screws 592 and 593, correspondingly, are covered by a fluid-repellent material. Without loss of generality, the fluid is water and the material, covering outer surfaces 596 and 597, is hydrophobic. Such a configuration, acting on the water surroundings by phobic-repulsive van der Waals forces, creates an outflowing water jetstream 595 moving dominantly along sagittal axis 594, wherein the whirling component of the motion is suppressed. Again, the motion occurs at the expense of the water warmth. The stationary pair of chiral screws: 592 and 593, can be considered as a whole and be interpreted as a hydrophobic-device 591 lunching jetstream 595.

(197) In view of the foregoing description with reference to FIGS. 5h, 5i, 5j, and 5k, it will be evident to a person skilled in the art that hydrophobic-device 590 and/or 591 can be supplied with a Peltier element, capable of operating as a thermoelectric generator producing electricity from the temperature difference caused by the hydrophobic jet-effect. As well, if asymmetrical airfoil blades 571 and/or 581 and/or 592 and/or 593 are capable of rotation, then the hydrophobic-repulsive force F.sub.hp results in rotations of the asymmetrical airfoil blades, and hydrophobic-propellers 570 and 580, as well as hydrophobic-devices 590 and/or 591 can be applied to electricity generation using a turbine-generator.

(198) In view of the foregoing description with reference to FIGS. 5e, 5h, 5i, 5j, and 5k, it will be evident to a person skilled in the art that hydrophobic-devices 512 and/or 590 and/or 591 can be cascaded sequentially and in-parallel, and a big submarine can be supplied with an aggregated jet-device, composed of many small hydrophobic-devices 512 and/or 590 and/or 591 and thereby providing a substantial cumulative jet-thrust.

(199) The pair of chiral screws: 592 and 593 generates a forced resulting acoustic wave propagating along sagittal axis 594. The forced resulting acoustic wave is composed of elemental acoustic waves originated by each ring of the screws.

(200) The inventor points out that a long screw, either alone as screw 576 shown in FIG. 5i, or combined as the pair of screws: 592 and 593, constructed to provide an in-phase superposition of a big number N of generated elemental acoustic waves, results in the constructive interference forming a combined acoustic wave, bringing the usable wave power that higher than the usable power of one elemental acoustic wave by the factor of N.sup.2.

(201) Aerodynamic and Hydrodynamic Effects

(202) In view of the foregoing description with reference to FIGS. 4, 5a, 5b, 5c, 5d, 5e, 5h, 5i, 5j, and 5k, it will be evident to a person skilled in the art that, considering flow as moving molecular fluid, when a flow portion is flowing around a body, the flow portion and body become subjected to the following main aerodynamic and hydrodynamic effects, differing in mechanism of originating: stagnation of the flow portion impacting the body resulting in drag of the body; sticking of the flow portion to the body resulting in skin-friction; attracting and thereby redirecting of the flow portion to a smoothly curved body surface, i.e. the Coanda-effect as a kind of jet-effect, resulting in a lift-force acting on the body; convective (i.e. jet-effect) self-acceleration, resulting in jet-thrust acting on the body, wherein the jet-thrust is vectored against the flow portion acceleration and hence, against the flow portion headway motion; an adiabatic compression and/or extension acting on the body by the static pressure and temperature variations, both changing adiabatically; the turbulence of the flow portion, swirling and vibrating the body and ambient surroundings; diffusion, interrelated with the osmotic-like partial pressure, resulting in penetrating the flow portion into the ambient molecular fluid and, vice-versa, in entrapping the ambient molecular fluid by the flow portion (this effect is also frequently called the Coanda-effect); hydrophobicity of the body, resulting in repelling the flow portion and thereby originating the hydrophobic jet-effect; and peculiar and forced oscillation of fluid portions, both being interrelated with the waving jet-effect and resulting in peculiar and forced acoustic waves, correspondingly.
All the effects contribute in the cumulative-inner-static-pressure acting on the boundaries of the flow portion. As the effects differ in mechanism of originating, the proportion of the mentioned effects action intensity may vary, depending on both: geometry of the body and velocity of the flow. In a certain situation, when the body has an airfoil shape, the component of jet-thrust may exceed the drag and skin-friction, thereby providing a positive net jet-thrust against the flow, as it occurs, for example, with a sailboat, when a point of sail belongs to the “close-hauled” group “B”, as described hereinabove with reference to FIG. 1i. As well, the generated as peculiar as well as forced acoustic waves, when superposed, constitute interference, the resulting wave power of which is acquired from the fluid warmth due to the waving jet-effect.
Electromagnetic Accompanying

(203) Reference is now made again to FIG. 5i, wherein now, the ambient fluid is a water-based electrolyte.

(204) The inventor points out that, in this case, each ring of spiral 576, acting as a source of a peculiar acoustic wave, generates also as a peculiar electromagnetic wave, as well, each pair of the neighbor rings acts as a source of a forced elemental electromagnetic wave. Furthermore, the sequential in-line arranged pairs of the neighbor rings of spiral 576 acts as an array of sources, generating a multiplicity of the forced elemental electromagnetic waves, which form spatial interference. For the sake of clarity, there are N rings in spiral 576 originating N forced elemental electromagnetic waves, correspondingly. Considering the elemental electromagnetic waves propagating along axis 579 only, when a pitch of spiral 576 is equidistant and thereby providing a certain time-delay interrelated with a phase-shift between the forced elemental electromagnetic waves, the multiplicity of the N forced elemental electromagnetic waves forms a constructive interference along the axis 579, where all the N forced elemental electromagnetic waves become superposed in-phase.

(205) The resulting electromagnetic wave, formed by the superposition of the forced in-phase elemental electromagnetic waves, brings the resulting usable wave power proportional to the second power of the resulting amplitude of the oscillating electric field. Hence, the cumulative usable wave power of the resulting electromagnetic wave is higher than the usable wave power of one elemental electromagnetic wave by the factor of N.sup.2 and is higher than the sum of usable wave powers of all the N elemental electromagnetic waves by the factor of N, wherein the self-acquired portion of the resulting electromagnetic wave power is self-extracted from the universe background energy (at least from the electromagnetic gas heat-like energy) stored in the space due to the electromagnetic waving jet-effect as described hereinabove: in relation to an electric flux, with the reference to prior art FIG. 1f, and in relation to an electromagnetic wave, in subparagraph “Hypothetic Electromagnetic Analogue”.

(206) The inventor points out that a specifically arranged sequence of sources of acoustic waves in an electrolyte that, in the final analysis, is the specifically arranged sequence of sources of elemental electromagnetic waves (for instance, similar to spiral 576 representing a helical antenna launching chiral circularly-polarized radio waves), when supplied with a detector of the resulting electromagnetic wave power as a power converter which is capable of transformation of the electromagnetic wave power into electric power, becomes capable of operating as a generator of electricity, producing the electric power from the universe background energy stored in the space occupied by the electrolyte due to the electromagnetic waving jet-effect.

(207) Constructive-Interference-Generator of Useful-Beneficial Power

(208) For the purpose of the present patent application, the term “useful-beneficial power” should be understood as either a jet-thrust power or electric power, which being useful and beneficial when used in industry.

(209) FIG. 5l is a schematic illustration of a generic portion 5.A of a constructive-interface-generator capable to produce a useful-beneficial power as an exemplary embodiment of constructive interference of two mutually synchronized electromagnetic waves. The generic portion 5.A comprises a two-arm converging waveguide conveying two waves into a common antenna to receive an in-phase superposition of the two waves. Namely, the generic portion 5.A comprises: Two identical energetically inter-independent feeders: 5.2A and 5.2B, powering two identical transmitting antennas: 5.1A and 5.1B, correspondingly, wherein: on the one hand, the two identical transmitting antennas: 5.1A and 5.1B, are energetically inter-independent; and on the other hand, the two identical transmitting antennas: 5.1A and 5.1B, are mutually synchronized to launch electromagnetic waves: 5.3A and 5.3B, each bringing the wave power W.sub.1, along identical primary waveguides 54.A and 5.4B, correspondingly, wherein the electromagnetic waves: 5.3A and 5.3B, both, for simplicity, being characterized by the same carrier frequency f and amplitude A.sub.1; A pair of the primary waveguides 5.4A and 5.4B being gradually joint into a single secondary waveguide 5.4C (thereby, forming the two-arm converging waveguide) such that the electromagnetic waves: 5.3A and 5.3B, becoming superposed providing for constructive interference forming the resulting electromagnetic wave 5.3C of amplitude A equal to the sum of two amplitudes A.sub.1, i.e. A=2A.sub.1; wherein, as the wave power is proportional to the second power of amplitude, the cumulative wave power W of the resulting electromagnetic wave 5.3C, being proportional to A.sup.2, is equal to W=4W.sub.1; and The receiving antenna 5.1C, receiving the resulting electromagnetic wave 5.3C, being conveyed by the secondary waveguide 5.4C and bringing the cumulative wave power W=4W.sub.1; wherein the receiving antenna 5.1C being capable of transformation of the wave power W into the electric power equal to (4W.sub.1) (if, hypothetically, to ignore effects of electric power dissipation into the warmth due to resistivity of conductive materials), released from the feeder output 5.2C.

(210) In view of the foregoing description referring to FIG. 5l, it will be evident to a person skilled in the art that the generic portion 5.A can be further developed to comprise an N-arm converging waveguide, instead of the two-arm converging waveguide, and so one can implement the constructive-interface-generator of useful-beneficial power by: combining a big number N of the energetically inter-independent feeders to power N transmitting antennas launching N elemental electromagnetic waves, correspondingly, each of which [the N elemental electromagnetic waves] bringing an elemental wave power portion of at least W.sub.1; controlling the mutual synchronization of the N transmitting antennas; and thereby using a set of waveguides to convey and combine the N mutually synchronized elemental electromagnetic waves, thereby, forming the resulting electromagnetic wave as constructive interference of the N elemental electromagnetic waves, thereby, bringing the cumulative wave power being higher than the elemental power portion W.sub.1 by the factor N.sup.2, wherein the harvested power portion, equal to ΔW.sub.N=N(N−1)W.sub.1, in the final analysis, being acquired at the expense of the ambient warmth.

(211) FIG. 5m is a schematic illustration of constructive-interference-generator 5.00 for producing the useful-beneficial power, constructed in accordance with the principles of the present invention. The constructive-interference-generator 5.00, in principle, similar to the constructive-interference-generator 5.A developed to have the N-arm converging waveguide described hereinabove referring to FIG. 5l, but now the embodiment 5.00 comprises an unclad waveguide 5.30 having a transparent shell. Namely, the constructive-interference-generator 5.00 comprises the following components: A set of N elemental feeders 5.21, 5.22, 5.23, . . . , 5.2N, being energetically inter-independently powered by a starter power; wherein to implement the set one can use either: a set of N internal combustion engines, as each of which being powered by burning a separate portion of fuel; and/or a set of N wind-turbines, as each of which being powered by a separate portion of the ambient wind; and/or a set of N solar radiation collectors (each of which being at least one of a solar thermal collector and a photovoltaic cell), as each of the N solar radiation collectors being powered by a separate portion of the Sun radiation; and/or a set of N whatever devices being powered by the starter power energetically inter-independently; A classic waveguide 5.30 of waves, for instance: the waves are electromagnetic waves characterized by the carrier frequency and wavelength, phase, amplitude, polarization, time-delay, and direction of propagation and, the classic waveguide 5.30 is an unclad dielectric pipe having a dielectric constant higher than the dielectric constant of ambient matter (for instance, ambient air); it will be evident to a person skilled in the art that the dielectric matter of pipe, being characterized by a relatively big dielectric constant, is inherently characterized by a big so-called refractive index thereby making the unclad dielectric pipe as a good waveguide for electromagnetic waves; A classic mutually specifically synchronized set 5.10 of N transmitting antennas 5.11, 5.12, 5.13, . . . , 5.1N, launching N elemental electromagnetic wave-power portions, 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly (for simplicity, of the same wave-power W.sub.1); wherein: the unclad shell of the classic waveguide 5.30 is transparent for the waves 5.31, 5.32, 5.33, . . . , 5.3N; and the classic specifically mutually synchronized antennas 5.11, 5.12, 5.13, . . . , 5.1N are arranged and oriented to enter the electromagnetic wave-power portions (simply saying, waves) 5.31, 5.32, 5.33, . . . , 5.3N, into the waveguide 5.30 at a sharp angle to the shell (i.e. almost the right angle of incidence), wherein the arrangement is such that certain intervals 5.42 between the antennas 5.11, 5.12, 5.13, . . . , 5.1N, providing for that, when the waves propagating within the waveguide 5.30, the waves 5.31, 5.32, 5.33, . . . , 5.3N become in-phase superposed thereby resulting in constructive interference; it will be evident to a person skilled in the art that the waves 5.31, 5.32, 5.33, . . . , 5.3N propagate within the wave-guide 3.30 along a zig-zag way due to the wave-guide effect and that, inside the waveguide 5.30, the inside angle of incidence of the waves on the waveguide 5.30's shell is equal to the angle of inside reflection and each inside reflection is accompanied by the phase-shift of the wave on 90°, and so the distance 5.42 is easily calculated to provide zig-zag pathway differences between the propagating waves 5.31, 5.32, 5.33, . . . , 5.3N equal to integer number of the carrier wavelengths, thereby, to provide the desired in-phase superposition of the waves 5.31, 5.32, 5.33, . . . , 5.3N propagating within the waveguide 5.30; and A classic receiving antenna 5.20, receiving the cumulatively-resulting wave 5.40, characterized by the amplitude greater than the amplitude of the single wave 5.31 by the factor N and characterized by the wave-power W.sub.N equal to W.sub.N=N.sup.2 (e.sub.1W.sub.1), where e.sub.1 is energetic net-efficiency of antenna 5.11 and (e.sub.1W.sub.1) is the wave power of the single wave 5.31; thus, the classic receiving antenna 5.20 releases the resulting power (e.sub.2W.sub.N), where e.sub.2 is energetic net-efficiency of power releasing from the receiving antenna 5.20 via the feeder output 5.43.
Thereby, it will be evident to a person studied the present patent application that: one enables to construct and embody an exemplary constructive-interference-generator, consuming the starter power W.sub.N1, equal to W.sub.N1=N×W.sub.1, with the net-efficiency of the consumption e.sub.1 to launch and enter the wave power of N×e.sub.1 W.sub.1 into the waveguide 5.30 and releasing the useful-beneficial power W.sub.N2 equal to W.sub.N2=e.sub.2N.sup.2e.sub.1W.sub.1; the exemplary constructive-interference-generator has a practical use, for instance, to harvest the acquired power portion equal to W.sub.N2−W.sub.N1=N(e.sub.1e.sub.2N−1)W.sub.1, wherein W.sub.N1=N×W.sub.1 is the consumed power, the power of N×e.sub.1 W.sub.1 is the wave power launched by the set of N antennas 5.10, W.sub.N2=e.sub.1e.sub.2N.sup.2×W.sub.1 is the power released from the feeder output 5.43, and the big number N provides for a positive difference W.sub.N2 W.sub.N1; and in the final analysis, the harvested portion of power is acquired at the expense of the ambient warmth.
Generalized Generator of Useful-Beneficial Power

(212) The foregoing description, expound hereinabove in subparagraphs: “Exemplary Implementation of Constructive Interference” referring to FIG. 5i, proposing a generator of electricity capable of producing the electric power from the ambient warmth due to the acoustic waving jet-effect; “Electromagnetic Accompanying” referring to FIG. 5i, proposing a generator of electricity capable of producing the electric power from the universe background energy due to the electromagnetic waving jet-effect; and “Constructive-Interference-Generator of Useful-Beneficial Power” referring to FIGS. 5l and 5m, proposing a constructive-interference-generator of electricity capable of producing the electric power acquired at the expense of the universe background energy due to the electromagnetic waving jet-effect;
is further summarized hereinbelow as a description of a generalized generator for producing a useful-beneficial power, constructed according to the principles of the present invention to harvest the useful-beneficial power from at least one of: the ambient warmth, in relation to the mechanic power of a moving molecular fluid and acoustic waves; and the universe background energy, in relation to the electromagnetic power of electromagnetic waves.
The term “generalized”, accompanying the term “generator” as well as accompanying terms characterizing components of the generalized generator, is used to emphasize that the term “generalized generator” and the terms specifying the mentioned components of the generalized generator have a wide sense assuming a diversity of implementations and triggered jet-effects.

(213) Reference is now made again to FIG. 5m, wherein now, it is a schematic illustration of the generalized generator 5.00 for producing the useful-beneficial power, constructed in accordance with the principles of the present invention.

(214) For the purposes of the generalization, a set of interrelated terms are defined as follows: (a) peculiar shock-like wave is defined as a reaction originated by a local acceleration of a fluid portion in a prevalent direction and as a peculiar wave, propagating in the accelerated headway-moving portion of fluid; (b) an elemental wave is defined as at least one of an acoustic wave and an electromagnetic wave; said elemental wave being at least one of said peculiar shock-like wave and a forced wave; (c) wave is defined as a complex wave being composed of elemental waves, wherein said wave being characterized by resulting amplitude defined as the vector sum of amplitudes of said elemental waves; (d) radiation jet-effect is defined as a phenomenon comprising two interrelated manifestations: of radiation pressure of wave, wherein the radiation pressure is at least one of acoustic and electromagnetic, and of wave energy traveling in a prevalent direction, wherein the wave energy is at least one of acoustic and electromagnetic; (e) acoustic waving jet-effect is defined as a kind of the Coanda-jet-effect, being applied to inner portions of fluid, as a tendency of an oscillatory moving-small-portion to be attracted to and aligned with a curvature of a nearby fragment of an imaginary boundary of said inner portion; (f) electromagnetic waving jet-effect is defined as a tendency of a certain spatial portion of an ambient electric field to be attracted to and aligned with a nearby surface interacting with the certain spatial portion of the ambient electric field, wherein said nearby surface is at least one of a real conductive wall and an imaginary wall formed by force-lines of the ambient electric field bordering the certain spatial portion; (g) waving jet-effect is defined as at least one of the acoustic waving jet-effect and the electromagnetic waving jet-effect; (h) phobic-repulsing jet-effect is defined as a kind of jet-effect, occurring in a fluid near to a surface made from a fluid-repellent material; (i) generalized jet-effect is defined as an effect of fluid portion convective acceleration at the expense of fluid portion internal heat energy that is inherently characterized by a decrease in original temperature of said fluid portion in an adiabatic process, wherein the generalized jet-effect is at least one of the Venturi effect, the Coanda-jet-effect, the acoustic waving jet-effect, the electromagnetic waving jet-effect, the radiation jet-effect, and the phobic-repulsing jet-effect; (j) a usable wave power is defined as a partial wave power of a complex wave being composed of elemental waves, being superposed and thereby resulting in partially constructive interference and partially destructive interference, wherein said partial wave power being proportional to the second power of the resulting amplitude of said wave, and hence being detectable by a classic detector of waves, reacting on the resulting amplitude of wave (i.e. being detectable by a classic receiving antenna); (k) a latent wave power is defined as a partial wave power of a complex wave being composed of elemental waves, being superposed and thereby resulting in partially constructive interference and partially destructive interference, wherein said partial wave power being undetectable by a classic detector of waves, reacting on the resulting amplitude of wave, and being detectable by a thermal detector (i.e. a thermometer and/or a thermographic camera), reacting on the local thermal radiation; (l) warmth of a molecular fluid is defined as a storage of the kinetic power of the fluid molecules; (m) the universe background energy is defined as a latent energy stored in space, wherein the universe background energy being composed of at least the latent electromagnetic energy; (n) fluid flow is defined as a molecular fluid, bringing the warmth and origin kinetic power of motion in a prevalent direction; (o) the specific M-velocity, indicated by M.sub.*, related to said fluid flow, is defined as equal to √{square root over ((γ−1)/γ)}, where γ is so-called adiabatic compressibility parameter of said molecular fluid; (p) the specific kinetic power, indicated by W.sub.*, is defined as kinetic power of fluid flow moving with the specific M-velocity M.sub.*; (q) raw power is defined as a power yet to be in a usable form; (r) a generalized stock of said raw power is defined as at least one of: the warmth of ambient fluid, storing the kinetic power of molecules, and the universe background energy, storing the latent electromagnetic energy; (s) a starter power, indicated by W.sub.external, is defined as at least one of: thermal power harvested from a burned fuel, external electric power, kinetic power of fluid flow, internal heat power of fluid flow, frequently called warmth of ambient fluid, and electromagnetic power brought by sunlight; (t) a generalized trigger of jet-effect is defined as a component of a system, said component being characterized by a field, being spread in ambient fluid medium and thereby making said system to be open from the thermodynamics point of view, wherein said component is at least one of: a fluid flow 5.41, to trigger at least one of the Venturi effect, the Coanda-jet-effect, and the waving jet-effect; wherein the mentioned field is a field of flow velocities; wherein, looking ahead in view of the description of subparagraph “Convergent-Divergent Jet-Nozzle” referring to FIG. 6a of the invention, it will become evident to a person studied the present invention that the relatively slow fluid flow 5.41, which yet can be accelerated by the Coanda-jet-effect, is characterized by M-velocity being lower than the specific M-velocity, indicated by M.sub.*, specified in equation (6.9); a fluid-repellent surface (for instance, similar to outer surface 577 of spiral 576 shown in FIG. 5i), to trigger the phobic-repulsing jet-effect, wherein the mentioned field is a field of repulsing forces; and an electromagnetic field, to trigger the electromagnetic waving jet-effect; (u) an airfoil convexity of a corpus exposed to said fluid flow is defined as a convexity being “embraced” by two edges in the direction of said fluid flow motion, namely: by a rounded leading edge, upstream of said fluid flow motion; and by a sharp trailing end, downstream of said fluid flow motion; thereby, providing airfoil properties of said corpus and hence providing that said airfoil convexity, when interacting with said fluid flow portion, causing a conversion of a portion of said fluid warmth into a portion of kinetic power acquired by said fluid flow portion due to the Coanda-jet-effect in an adiabatic process; said portion of kinetic power acquired by said fluid flow portion due to the Coanda-jet-effect in an adiabatic process: when manifested as a power, supporting an upward motion, is further called a lift-force power, and when manifested as a power, supporting an forward motion, s further called a jet-thrust power; (v) a generalized elemental source launching an elemental usable power portion of at least W.sub.1 is defined as a device transforming an elemental pre-usable power portion, into said elemental usable power portion of at least W.sub.1; wherein the generalized elemental source is at least one of: an airfoil convexity of a corpus exposed to a fluid flow portion moving nearby said airfoil convexity (for instance, similar to outer surface 577 of spiral 576 shown in FIG. 5i), wherein said elemental pre-usable power portion is composed of an original internal heat power of fluid flow and original kinetic power of fluid flow; and wherein said elemental usable power portion, equal to at least W.sub.1, is specified as the kinetic power of fluid flow composed of the original kinetic power of fluid flow and an additional portion of kinetic power acquired in an adiabatic process due to at least one of the Venturi effect and the Coanda-jet-effect; an antenna of acoustic waves, capable of a receiving said elemental pre-usable power portion, equal to at least W.sub.1 and a launching an acoustic wave bringing said elemental usable power portion of at least W.sub.1; and an antenna of electromagnetic waves, capable of a receiving said elemental pre-usable power portion, equal to at least W.sub.1 and a launching an electromagnetic wave bringing said elemental usable power portion of at least W.sub.1; (w) a generalized elemental feeder is defined as an interface of power between said generalized stock and said generalized elemental source, wherein said interface consuming said starter power W.sub.external and being capable of conversion said raw power, extracted from said generalized stock, into said elemental pre-usable power portion and supplying the elemental pre-usable power portion to said generalized elemental source launching said elemental usable power portion of at least W.sub.1, wherein said generalized elemental feeder being at least one of: said airfoil convexity of the corpus exposed to a portion of fluid flow 5.41 moving nearby said airfoil convexity (note, the airfoil convexity plays the role of both said elemental source and said elemental feeder) exposed to said fluid flow 5.41; thereby, causing that: (i) a portion of origin kinetic power, indicated by W.sub.0, brought by said fluid flow portion yet to be subjected to the Coanda-jet-effect, being lower than the specific kinetic power W.sub.*, and coming to said airfoil convexity, and (ii) the kinetic power, indicated by δW.sub.1, of said fluid flow portion, acquired due to the Coanda-jet-effect in an adiabatic process, both constitute said elemental pre-usable power portion, indicated by W.sub.1=W.sub.0+8W.sub.1, remaining lower than the specific kinetic power W.sub.* and being higher than W.sub.0 at least by factor F.sub.1 to satisfy the condition: F.sub.1W.sub.0=W.sub.1<W.sub.*; a generalized engine providing powering an antenna of acoustic waves by said elemental pre-usable power portion of at least W.sub.1; and a generalized engine providing powering an antenna of electromagnetic waves by said elemental pre-usable power portion of at least W.sub.1; (x) a generalized jet-converter of power is defined as an aggregation comprising a conductor 5.30 of traveling power and a gathering of N said generalized elemental sources (marked by set 5.10 of numerals: 5.11, 5.12, 5.13, . . . , 5.1N) launching corresponding N said elemental usable power portions (marked by numerals 5.31, 5.32, 5.33, . . . , 5.3N), wherein said aggregation (5.30 and 5.10) providing an operation of said N generalized elemental sources 5.10 (5.11, 5.12, 5.13, . . . , 5.1N) in unison, thereby making said generalized jet-converter of power being capable of a transformation said raw power into said useful power 5.40, wherein said transformation is implemented using a multi-stage repeating of said generalized jet-effect provided by said generalized trigger of jet-effect; said aggregation is at least one of: an aggregation of a conductor 5.30 of flow and N said airfoil convexities, sequentially arranged to be exposed to said fluid flow portion, moving along said conductor of flow and coming to said N airfoil convexities and flowing around said N airfoil convexities sequentially, thereby, said aggregation providing a sequential multi-stage repeated action of said N airfoil convexities on said fluid flow portion resulting in a corresponding multi-stage repeating of the Coanda-jet-effect operation applied to said transformation of said raw power into said useful power, indicated by W.sub.N, in the form of kinetic power of a resulting jetstream; thus, while said useful power remaining substantially lower than the specific kinetic power W.sub.*, said useful power W.sub.N 5.40 of said resulting jetstream is higher than said portion of origin kinetic power, indicated by W.sub.0, brought by said fluid flow portion 5.41 yet to be subjected to the Coanda-jet-effect, by the factor of at least F.sub.1.sup.N; an aggregation of a waveguide 5.30 and N said antennas of waves, specifically arranged and mutually synchronized to launch N in-phase waves, correspondingly, and thereby to provide constructive interference of said N in-phase waves within said waveguide, wherein each of said N waves bringing said elemental usable power portion of at least W.sub.1 thereby providing that said constructive interference of N said waves thereby subjected to the waving jet-effect, in-phase reinforced repeatedly N times, thereby forming a resulting wave bringing said useful power 5.40 in form of wave power of at least W.sub.N being higher than the elemental usable power portion W.sub.1 by the factor of N.sup.2; and wherein, without loss of generality but for the sake of concretization, the mutual synchronization of the N sources 5.11, 5.12, 5.13, . . . , 5.1N of waves 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly, is implemented applying certain delays, for instance, using a certain intervals 5.42 between the sources 5.11, 5.12, 5.13, . . . , 5.1N, thereby providing for that, when propagating within waveguide 5.30, the waves 5.31, 5.32, 5.33, . . . , 5.3N become in-phase superposed thereby resulting in constructive interference; and (y) a generalized power converter 5.20 is defined as an engine providing a mechanism for a reincarnation of said useful power 5.40 into said useful-beneficial power, wherein said engine is at least one of: open space, thereby providing conditions for reincarnation of said useful power W.sub.N of said resulting jetstream into said jet-thrust power, according to Newton's Third Law; a turbo-generator (shown schematically as a generalized antenna 5.20), capable of transformation said useful power W.sub.N of said resulting jetstream 5.40 into the electric power released from the feeder output 5.43; a Peltier element operating as a thermoelectric generator, primary producing electricity from the temperature difference caused by said generalized jet-effect; and a generalized receiving antenna 5.20 having the feeder output 5.43, wherein said generalized receiving antenna 5.20 being capable of conversion said useful power W.sub.N 5.40 of said resulting wave 5.40 into the electric power 5.43, and wherein said feeder output 5.43 providing the electric power release.
The generalized generator 5.00 comprises the following generalized constituent elements: a generalized starter, being composed of: said ambient fluid medium; N generalized elemental feeders, enumerated by 5.21, 5.22, 5.23, . . . , 5.2N, being energetically inter-independently powered; and a generalized stock of raw power, storing the power yet to be in a usable form; said generalized trigger of the generalized jet-effect; said generalized jet-converter of power, comprising an aggregation of a conductor 5.30 of traveling power and a gathering 5.10 of N generalized elemental sources, enumerated by 5.11, 5.12, 5.13, . . . , 5.1N, launching N elemental usable power portions, enumerated by 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly; wherein the triple-dots, having numerals 5.14 and 5.24: symbolize the conformance between the N generalized energetically inter-independent feeders and the N generalized elemental sources of the N elemental usable power portions correspondingly, as well as say that, preferably, N is a certain big number, wherein the big integer number N having the claimed sense is at least 10; and said generalized power converter 5.20 transforming said useful power into said useful-beneficial power.

(215) In relation to electromagnetic waves, without loss of generality but for the sake of concretization only, the waveguide 5.30 is characterized by a high dielectric constant, higher than the dielectric constant of the ambient medium, wherein the high dielectric constant provides for the condition of the so-called total internal reflection of the electromagnetic waves, i.e. providing for a hypothetically ideal lossless waveguide effect.

(216) In relation to both: the acoustic waves and the electromagnetic waves, each of the N sources 5.11, 5.12, 5.13, . . . , 5.1N of waves 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly, consumes the power W.sub.0 and launches a wave (one of 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly) bringing the wave power W.sub.1. Speaking strictly, as it follows from the description expound hereinabove in subparagraphs “Interference of Acoustic Waves” and “Hypothetic Electromagnetic Analogue”, the consumed power W.sub.0 differs from the wave power W.sub.1 brought by the wave, wherein the difference (W.sub.1−W.sub.0), on the one hand, is defined by a positive power portion acquired due to the waving jet-effect and radiation jet-effect and, on the other hand, is defined also by a negative power portion lost due to wave power dissipation in the ambient medium. When ignoring the negative power portion, one usually interprets that W.sub.1=W.sub.0, just ignoring the work for the wave energy travelling itself that must be supported by a certain power according to The Energy Conservation Law. The mentioned positive power portion, harvested due to the waving jet-effect, goes for the wave energy travelling. Normally, the consideration of the wave power without the power consumption for the wave energy traveling itself is justified when one estimates a useful-beneficial power only.

(217) The inventor emphasizes that sources 5.11, 5.12, 5.13, . . . , 5.1N of waves 5.31, 5.32, 5.33, . . . , 5.3N, correspondingly, are fed energetically inter-independently. For example, each of the sources consumes the power from a separate generalized generator of electrical signals to feed the corresponding wave. Alternatively, a feeding, using different periods of a wave, is also interpreted as energetically inter-independent; but in contrast, a “multi-source” feeding, implemented by means of a splitting of high power, cannot be interpreted as an inter-independent feeding.

(218) The inventor points out that the importance of the energetic inter-independence of the sources 5.11, 5.12, 5.13, . . . , 5.1N is predetermined by the reciprocity theorem, which, when applied to the case, saying that, when a parent wave, bringing the usable wave energy U.sub.N per wavelength, is subjected to a decomposition thereby forming N coherent daughter waves, each daughter wave brings the usable wave energy U.sub.1 per wavelength that is lower than the parent usable wave energy U.sub.N per wavelength by the factor N.sup.2, but not by the factor N, wherein the lack of the wave energy, equal to ΔU.sub.N=N(N−1)U.sub.1, becomes transformed into the latent energy of the ambient medium (in the case of electromagnetic waves, the ambient medium is the vacuum filled by the universe background energy, comprising the latent energy of “electromagnetic gas”).

(219) Thus, considering actually energetically inter-independent sources 5.11, 5.12, 5.13, . . . , 5.1N, for the sake of simplicity, ignoring the difference between W.sub.0 and W.sub.1, the sum power W.sub.N1, consumed by the N energetically inter-independently fed sources 5.11, 5.12, 5.13, . . . , 5.1N, is equal to W.sub.N1=NW.sub.1. The mutual synchronization of the N sources 5.11, 5.12, 5.13, . . . , 5.1N of waves 5.31, 5.32, 5.33, . . . , 5.3N is implemented applying certain delays, for instance, using certain intervals 5.42 between the sources 5.11, 5.12, 5.13, . . . , 5.1N, thereby providing for that, when propagating within waveguide 5.30, the waves 5.31, 5.32, 5.33, . . . , 5.3N become in-phase superposed thereby resulting in constructive interference. The constructive interference is the resulting extra-high power wave 5.40 characterized by the increased amplitude (for instance, the amplitude of oscillating electric field), wherein the amplitude increase is specified by the factor N that corresponds to the resulting wave power W.sub.N2 equal to W.sub.N2=N.sup.2W.sub.1=NW.sub.N1.

(220) The inventor points out to the power difference between W.sub.N2 and W.sub.N1, namely, (W.sub.N2−W.sub.N1)=N(N−1)W.sub.1. In the case of acoustic waves, the power difference is acquired at the expense of the molecular fluid warmth, and in the case of electromagnetic waves, the power difference is acquired at the expense of the universe background energy (at least at the expense of the latent electromagnetic energy stored in the electromagnetic gas). Without loss of generality, the generalized power converter 5.20 is implemented as an antenna, exposed to the extra-high power wave 5.40. Generalized power converter 5.20 is capable of conversion of the extra-high power W.sub.N2 of wave 5.40 into the electric power released from feeder output 5.43 of generalized detector 5.20.

(221) The generalized generator is an open system from the point of view of thermodynamics interacting with the ambient matter and warmth. One of the primary features of the generalized generator is that it interacts with the ambient matter and warmth multi-stage repeatedly using a set of a big number N of generalized elemental feeders being energetically inter-independently powered and a set of the big number N of generalized elemental sources launching usable power portions.

(222) The inventor points out that, in contrast to the resonance electrical scheme of Tesla coil applied to induced oscillating electrical current to enable a radiation of super-impressive lightning impulses, the proposed superposition of N in-phase electromagnetic waves (wherein N is a specified number), to provide for the desired constructive interference bringing usable wave power, is easily controllable.

(223) Gravity-Jet Engine

(224) FIG. 5n is a schematic illustration of motionless gravity-jet engines: 5.50 and 5.60, each comprising an elaborated airfoil shaped container: gauge 5.51 and primary 5.61, correspondingly, being permanently filled with liquid (for instance, water) 5.70 characterized by the density, substantially higher than the density of ambient gas (for instance, air). The upper surface of water in each of containers: 5.51 and 5.61, is on level 5.71 and has a cross-sectional area A.sub.0 5.72. The inner side of the container walls is hydrophobic (to reduce the walls resistance) and the elaborated airfoil shape of each of containers: 5.51 and 5.61, provides the condition of a cross-sectional area decrease in the vertical direction from the value A.sub.0 5.72 to the value A.sub.1 5.73 that (the decrease) corresponds to the cross-sectional area decrease for water, which is freely falling in the gravitational field.

(225) The inventor points out that the freely falling of fluid occurs with an acceleration, which differs from the gravitational acceleration of a material point (or sold body) by an additionally acquired acceleration, because of two accompanying effects, namely: a part of potential energy goes for a work for deformation of the falling fluid portions, which (the deformation) results in elongation of water portions in the vertical direction, i.e. results in the acquired acceleration by definition, and, in turn, the fluid portions deformation in combination with the fluid motion is inevitably accompanied by the Venturi effect having the jet-effect nature, thereby providing for the additionally acquired acceleration at the expense of the internal heat of the fluid.

(226) The gauge container 5.51 is supplied with gauge curved convergent-divergent nozzle 5.52 and the primary container 5.61 is supplied with primary curved converging nozzle 5.62, wherein the volume of the container (5.51 or 5.61) is much bigger than the volume of nozzle (5.52 or 5.62, correspondingly) to ignore of the moving water pulse change when considering the water stream changing the velocity vector within the curved nozzle (5.52 or 5.62, correspondingly). Wherein: The gauge convergent-divergent nozzle 5.52 is beginning from cross-section 5.73 and leading to gauge-ending cross-section 5.53, wherein the beginning and ending cross-sections: 5.73 and 5.53, correspondingly, both have an identical area equal to A.sub.1 and both are located at the same level 5.74, which is lower than level 5.71 on height h.sub.0 5.75; and moreover, the varying cross-section of the convergent part is adapted to freely descending water and the divergent part is aligned inversely to the convergent part (i.e. adapted to freely ascending and retarding water); and The primary converging nozzle 5.62 having an elaborated airfoil cross-section beginning from cross-section 5.73 and leading to primary-ending cross-section 5.63, wherein the both cross-sections are at the same level 5.74 such that the distance between levels 5.71 and 5.74 equals h.sub.0 5.75; and wherein the area A.sub.1 of beginning cross-section 5.73 is greater than the area A.sub.2 of primary-ending cross-section 5.63 by the factor F of constriction, i.e. A.sub.1=F×A.sub.2. Looking ahead, the equations (6.13) and (6.14), described hereinbelow in subparagraph “Convergent-Divergent Jet-Nozzle” with reference to FIG. 6a, when applied to a fluid flowing through an elaborated actually-airfoil convergent-divergent jet-nozzle with extremely low M-velocities, is applicable to proper design of the mentioned elaborated airfoil converging nozzle 5.62 to provide for the water stream laminarity when the water stream is subjected to the Venturi effect. This means that to implement the constriction factor, for instance, F=2, and, at the same time, to provide for the laminarity of fluid flowing through the converging nozzle, one has to apply equation (6.14) to provide for the desired linear (or at least substantially gradual) change of the fluid static pressure.

(227) The water, which is located in each of elaborated airfoil shaped containers 5.51 and 5.61 above level 5.74, performs a gravity compressor (with respect to nozzles 5.52 and 5.62, correspondingly) operating in the gravitational field having force-lines in the vertical direction.

(228) The gauge nozzle 5.52 and the primary nozzle 5.62, both provide for an outflowing water jetstream, moving through the ambient air in the gravitational field and associated with trajectory: gauge 5.55 and primary 5.65, correspondingly.

(229) Ignoring the dragging effects acting by ambient air on a water jetstream as well as ignoring the mentioned additionally acquired acceleration due to the accompanying Venturi effect, the trajectory of water jetstream: either gauge 5.52 or primary 5.62, is described by parabola expressed with respect to butt-end point: either 5.56 or 5.66, correspondingly, as:

(230) $\begin{matrix} y = tg (θ) \times x - \frac{g}{2 u^{2} \cos^{2} θ} x^{2}, & Eq . (5.11 a) \end{matrix}$
where x and y are coordinates in the horizontal and vertical directions, correspondingly, θ is angle (either 5.57 or 5.67) between the vector velocity of jetstream associated with trajectory (either 5.55 or 5.65, correspondingly) at butt-end point (either 5.56 or 5.66, correspondingly) and a horizontal axis, g is gravitational acceleration, and u is the absolute velocity: either u.sub.1 or u.sub.2, of headway motion of the outflowing jetstream associated with trajectory: either 5.55 or 5.65, correspondingly, at the butt-end point: either 5.56 or 5.66, correspondingly.

(231) The absolute velocity u is determined by the height h.sub.0 5.75 and expressed by:
u=(1−ψ)√{square root over (Ψ2gh.sub.0)} Eq. (5.11b),
according to Torricelli's law, where the factors Ψ and ψ are introduced, wherein: the introduced factor of effective acceleration increase Ψ characterizes the mentioned interrelated effects: the accompanying Venturi effect and a change in internal heat of the unbrokenly and laminarly moving water with respect to the heat of a water portion in container (5.51 or 5.61) near the surface 5.72, wherein the effective acceleration increase Ψ is averaged over the height h.sub.0 when the water motion is steady-state. The deformation of the moving water portions shape results in a change in the water portions thermodynamic state. In particular, when the shape of a water potion becomes conic, the absolute velocity u has two orthogonal components: of a headway motion u.sub.H and of a cross-sectional collapsing u.sub.C, wherein the condition u=√{square root over (u.sub.H.sup.2+u.sub.C.sup.2)} is satisfied. The headway motion component u.sub.H characterizes the water flow Φ=ρu.sub.H, where ρ is the density of substantially incompressible water, while the cross-sectional collapsing component u.sub.C characterizes a water portion acquired acceleration, wherein the acquired acceleration occurs at the expense of either potential energy stored in the gravitational field and/or internal heat energy stored in the Brownian motion of fluid molecules. The cross-sectional collapsing component u.sub.C of freely falling water, defined as u.sub.C=0.5×dD/dt, where D is the effective linear size of cross-section (for instance, the diameter of a circle cross-section), is approximately estimated by:

(232) $\begin{matrix} u_{c} \approx \frac{g \sqrt{{Au}_{H}}}{4 \sqrt{π} \sqrt[4]{u_{H}^{2} + 2 gh}} \approx \frac{g \sqrt{{Au}_{H}}}{4 \sqrt{π} \sqrt[4]{2 gh (Ψ + 1)}}, & Eq . (5.11 c) \end{matrix}$ where A is the cross-sectional area at the height level h. The condition Ψ=1 is applicable, for instance, to a falling small drop or to water in a container having a uniform cross-section, where, hypothetically, the water descends laminarly and forcibly without the cross-sectional collapsing and so without acceleration. The condition u.sub.C>0 inevitably interrelates with the condition Ψ>1. The value of the effective acceleration increase factor Ψ is quantified hereinbelow in equations (5.11i) and (5.11k); and the introduced factor of velocity reduction ψ (0≤ψ≤1) characterizes loss of the water stream headway motion kinetic energy due to the dragging effects and turbulence within the container (5.51 or 5.61) and nozzle (5.52 or 5.62). A not-optimized shape of the container and nozzle results in the turbulence, which, in turn, results in dividing the kinetic energy of the water stream between the kinetic energy of headway motion and the kinetic energy of turbulent motion. The skin-friction between the moving water and nozzle, on the one hand, results in a decrease of the kinetic energy of water stream within the container and nozzle, and on the other hand, contributes to the turbulence. When the accelerated motion of water within the container is turbulent and the nozzle is resistive for the water motion, the factor of velocity reduction if, becomes significant. Hypothetically ignoring the dragging effects and the turbulence within the container and nozzle, the factor of velocity reduction if, equals zero.

(233) The mentioned elaborated airfoil shape of the container (5.51 or 5.61) and the inner surface of walls being hydrophobic, altogether provide that the condition ψ=0 is satisfied between levels 5.71 and 5.74. On the other hand, to define the effective acceleration increase factor Ψ, two fundamental laws: the equation of continuity and the Bernoulli theorem (the energy conservation law), are applied to the unbrokenly falling water. Namely, the velocity values u.sub.0H and u.sub.1H, where u.sub.0H and u.sub.1H are the components of water headway (in the case, dominantly vertical) motion velocities at cross-sections 5.72 and 5.73, correspondingly, are interrelated by the equation of continuity, namely:
A.sub.1u.sub.1H=A.sub.0u.sub.0H Eq. (5.11d).
The absolute velocities u.sub.0 and u.sub.1, both comprising also corresponding cross-sectional collapsing components, are interrelated by the Bernoulli theorem, for instance, written in the form of equation (5.10b), namely,

(234) $\begin{matrix} \frac{u_{0}^{2}}{2} + {gh}_{0} = \frac{u_{1}^{2}}{2} + R Δ T, & Eq . (5.11 e) \end{matrix}$
where R is specific fluid constant, and ΔT is the change in the absolute temperature of moving water that is determined by the cross-sectional collapsing component of the moving water velocity. Therefore,

(235) 0 ${\begin{matrix} \frac{u_{0 C}^{2}}{2} = \frac{u_{1 C}^{2}}{2} + R Δ T & Eq . (5.11 f) \\ \frac{u_{0 H}^{2}}{2} + {gh}_{0} = \frac{u_{1 H}^{2}}{2} & Eq . (5.11 g) \end{matrix}$
Combining equations (5.11d) and (5.11g), one obtains:

(236) $\begin{matrix} u_{1 H}^{2} = 2 {gh}_{0} \frac{A_{0}^{2}}{A_{0}^{2} - A_{1}^{2}} . & Eq . (5.11 h) \end{matrix}$
Comparing (5.11h) and Torricelli's law, written in the form of equation (5.11b), the effective acceleration increase factor Ψ on the height h.sub.0 is expressed by:

(237) $\begin{matrix} Ψ = (\frac{A_{0}^{2}}{A_{0}^{2} - A_{1}^{2}}) . & Eq . (5.11 i) \end{matrix}$
The equation (5.11i) makes it evident that the effective acceleration increase factor Ψ is greater than 1 for the case. The area A.sub.1 of the cross-section 5.73, specified for freely falling water, related to the height h.sub.0 and velocity u.sub.0H at cross-section 5.72, is expressed by:

(238) $\begin{matrix} A_{1} = \frac{A_{0} u_{0 H}}{\sqrt{u_{0 H}^{2} + 2 Ψ {gh}_{0}}} . & Eq . (5.11 j) \end{matrix}$
Using again the equation of continuity Eq. (5.11d) and the Bernoulli theorem Eq. (5.11g), and taking into account equation (511j) for the area A.sub.1 in equation (5.11i), the effective acceleration increase factor Ψ is expressed via u.sub.0H and h.sub.0, namely,

(239) $\begin{matrix} Ψ = \frac{1}{2} + \sqrt{\frac{1}{4} + \frac{u_{0 H}^{2}}{2 {gh}_{0}}} . & Eq . (5.11 k) \end{matrix}$
Thereby, the effective acceleration increase factor Ψ is estimated as:

(240) $Ψ = {\begin{matrix} Ψ > 1 & , & if {gh}_{0} > 0 & , & i . e . falling \\ Ψ = 1 & , & if {gh}_{0} = 0 & , & i . e . u_{0 H} = 0 \\ 0 < Ψ < 1 & , & if {gh}_{0} < 0 & , & i . e . upping \end{matrix}$
The inventor points out that, based on two fundamental laws: the equation of continuity and the energy conservation (the Bernoulli theorem), both applied to the unbrokenly falling water, the summary that the water stream free falling with an acceleration higher than the gravitational acceleration g is one of the primary teachings of the present invention.

(241) The absolute velocity of water moving through cross-section 5.73 is estimated as:

(242) $\begin{matrix} u_{1} = \sqrt{u_{1 H}^{2} + u_{1 C}^{2}}, where u_{1 H}^{2} = 2 Ψ {gh}_{0} and u_{1 C}^{2} \approx \frac{1}{16 π} \frac{g^{2} A_{0} u_{0 H}}{\sqrt{2 {gh}_{0} (Ψ + 1)}} \approx \frac{1}{16 π} \frac{g^{2} A_{0} u_{0 H}}{\sqrt{u_{H}^{2} + 2 gh}} . & Eq . (5.11 l) \end{matrix}$

(243) The shape of nozzle 5.52 has the varying cross-sectional area adapted to freely descending and freely ascending water such that thermodynamic states of water in positions 5.73 and 5.53 are identical. Thereby, the velocity of water portion at position 5.56 is equal to u.sub.1 specified by equation (5.11l). The maximal height h.sub.1 5.58 of the water jetstream associated with trajectory 5.55 is equal to h.sub.1=(u.sub.1H sin θ).sup.2/(2Ψg), wherein when θ=60°, ψ≈1, and ψ=0, then h.sub.1=0.75h.sub.0. The condition h.sub.1<h.sub.0 is satisfied.

(244) In contrast to nozzle 5.52, nozzle 5.62 is asymmetrical, having the area A.sub.1 of cross-section 5.73 bigger than the area A.sub.2 of primary-ending cross-section 5.63 by the factor F of constriction, i.e. A.sub.1=F×A.sub.2. Nozzle 5.62 provides for the Venture effect (having the jet-effect nature) and so providing for a convective acceleration of the portion moving through the nozzle such that velocity u.sub.2 at point 5.66 becomes higher than the velocity u.sub.1 at position 5.73 by the factor F, i.e. u.sub.2=F×u.sub.1 in accordance with the equation of continuity, wherein the velocity increase occurs at the expense of the water warmth.

(245) The mentioned condition that the volume of container 5.61 is much bigger than the volume of nozzle 5.62, justifies the assumption that the velocity u.sub.1 of water motion at the position 5.73 of both containers 5.51 and 5.61 is the same. Further, in accordance with the Bernoulli theorem applied to the water streaming through nozzle 5.62, the values u.sub.1 and u.sub.2 are interrelated as:

(246) $\frac{u_{1}^{2}}{2} = \frac{u_{2}^{2}}{2} + R Δ T$
where the negative value of the water absolute temperature change ΔT provides for the contribution to the kinetic energy of the outflowing water jet-stream.

(247) The increased velocity u.sub.2=F×u.sub.1 corresponds to another parabolic trajectory of the water jetstream 5.62. If, hypothetically, if, =0 and, for example, angle 5.66 equals Φ.sub.2=60° and the factor of constriction equals F=2, then the maximal height h.sub.2 5.68 of water jetstream 5.62 equals h.sub.2=F.sup.2h.sub.1=3h.sub.0.

(248) The inventor points out that the condition h.sub.2>h.sub.0 becomes reachable when the Venturi effect is triggered keeping the water motion laminar. Therefore, use of the height h.sub.2 5.68 of a waterfall for producing the electric power using a hydro-turbine [not shown here] is more efficient than a use of the original height h.sub.0 5.75. Furthermore, the height difference (h.sub.2−h.sub.0) 5.76 allows for the electricity harvesting and wherein reverting a falling water portion back into container 5.61 [not shown here] and thereby avoiding consumption of the water from container 5.61. For such a permanent use of the water portion, the water must permanently be consuming caloric, for instance, from ambient warmth. The inventor points out that this is not a so-called “Perpetuum mobile”, but the use of water heat and the heat of ambient air to produce useful power, strictly according to the Energy Conservation Law.

(249) The inventor points out that the described technique allowing for the transformation of water warmth into useful energy is composed of two obvious transformations: a gravitational acceleration of water stream in the Earth gravitational field; and a convective acceleration of water jetstream using an elaborated airfoil nozzle;
wherein the combination of the two obvious transformations provides for a new quality of motionless gravity-jet engine 5.60. Namely, this allows for the harvesting of useful power from the heat of water. The combination of a gravity compressor and an elaborated airfoil converging (or convergent-divergent) nozzle is one of the primary teachings of the present invention. Further, it will be evident for a person studied the present invention that: motionless gravity-jet engine 5.60 launching water jetstream 5.65, as a waterfall, is applicable to a hydro-turbine; wherein, the motionless gravity-jet engine, when operating in a mode reverting water portions back into container 5.62 and if the falling water is further powers the hydro-turbine (which, in the final analysis, producing electric power at the expense of the water warmth), at the same time, allows for cooling the water almost reaching the freezing point; motionless gravity jet engine 5.60 can be cascaded multi-stage repeatedly (implementing a hydro-gateway) to increase the cumulative height of waterfall; and, looking ahead, the equation (6.14), mentioned hereinabove and described hereinbelow in subparagraph “Convergent-Divergent Jet-Nozzle” with reference to FIG. 6a, in particular, assuming Venturi M-velocities (where the term “Venturi M-velocity” will be introduced), is applicable to design an elaborated shape of airfoil container 5.61, to provide an additionally acquired acceleration and laminarity of water motion.
Enhanced Transformer

(250) FIG. 5o is a schematic illustration of two transformers of alternating electrical voltage and current, namely, of: gauge transformer 5.8, comprising: an equi-cross-sectional electro-conductive and magneto-boosting core 5.81, being made from a material characterized by a high magnetic permeability (for instance, made from a ferromagnetic or ferrimagnetic material) and having a ring-like closed toroidal-like shape, symmetrical with respect to axis 5.80, and a pair of inter-isolated electro-conductive-coils: primary winding 5.82 and secondary winding 5.83, each coiling around the toroidal-like core 5.81, thereby, the gauge transformer, essentially, is an ordinary transformer of alternating electrical voltage and current, wherein the primary winding 5.82, when subjected to the alternating electrical voltage, is an input and the secondary winding 5.83, when electrically loaded, is an output of electric power; and enhanced transformer 5.9, comprising: a convergent-divergent electro-conductive and magneto-boosting core 5.91, being made from the ferromagnetic or ferrimagnetic material and having a varying-cross-sectional ring-like closed toroidal-like shape, asymmetrical with respect to axis 5.90, and a pair of inter-isolated electro-conductive-coils: primary winding 5.92 and secondary winding 5.93, each coiling around the asymmetrical toroidal-like electro-conductive and magneto-boosting core 5.91, constructed according to an exemplary embodiment of the present invention.

(251) Each of the primary electro-conductive-coil windings: 5.82 and 5.92, comprising electron gas composed of free electrons, is subjected to an applied alternating external voltage, called primary voltage, accompanied by an alternating primary current, in turn, originating alternating magnetic flux marked by force-lines of the magnetic field strength: 5.84 and 5.94, correspondingly. Although the magnetic field strength force-lines: either 5.84 or 5.94, is shown in one direction (clockwise), it actually alternates the direction with the alternating current in the primary electro-conductive-coil winding: either 5.82 or 5.92, correspondingly.

(252) Each of the closed toroidal-like cores: symmetrical equi-cross-sectional 5.81 and asymmetrical convergent-divergent 5.91, performs a closed “tunnel-corridor”, characterized by the high magnetic permeability and by low coercivity and destined for conveying the magnetic field power along the closed tunnel-corridor, in particular, from the location of primary electro-conductive-coil winding: ether 5.82 or 5.92, to the location of secondary electro-conductive-coil winding: either 5.83 or 5.93, correspondingly, wherein the shape of the closed tunnel-corridor, being either: ring-like symmetrical equi-cross-sectional 5.81, i.e. having identical cross-sections 5.85 and 5.86; or ring-like asymmetrical convergent-divergent 5.91, i.e. having relatively thick and thin portions with cross-sections 5.95 and 5.96, correspondingly, differing in area;
is sufficiently airfoil to assume that the originated alternating magnetic flux: either 5.84 or 5.94, correspondingly, is laminar along the closed tunnel-corridor: either 5.81 or 5.91, correspondingly, having no substantial vortices.

(253) The principal difference between the two transformers: gauge 5.8 and enhanced 5.9, is in symmetry and in cross-sectional area varying of the closed cores: ring-like symmetrical equi-cross-sectional 5.81 and asymmetrical convergent-divergent 5.91, correspondingly. The asymmetrical convergent-divergent core 5.91 has a gradually-varying cross-sectional area, indicted by A and interrelated with gradually-varying relative concentration of the magnetic field strength force-lines, providing the enhanced Venturi-like jet-effect applied to the alternating magnetic flux 5.94, magnetic field strength current value of which, appearing at the gradually varying cross-sectional area A, is indicted by H.

(254) Further, for the sake of relevant simplicity, omit the mentioning about the electromagnetic parameters alternation as well as omit the effects of electromagnetic power dissipation due to resistance to the magnetizing hysteresis because of the non-zero coercivity, due to turbulence of eddy currents within the toroidal-like cores as well as due to electrical resistance of the primary and secondary electro-conductive-coils.

(255) The inventor points out that the magnetic flux, indicated by Φ, of the magnetic field 5.94 is constant along the closed asymmetrical convergent-divergent tunnel-corridor 9.91, wherein the gradually-varying cross-sectional area A determines the gradual variation of the magnetic field 9.94's strength H, according to the equation of continuity applied to the magnetic flux, namely: Φ=A×H=Const. I.e. the narrowed cross-section 5.96 comprises an increased magnetic field strength H characterized by an increased relative concentration of the magnetic field strength force-lines and the widened cross-section 5.95 comprises a decreased magnetic field strength H characterized by a decreased relative concentration of the magnetic field strength force-lines. Furthermore, the constant magnetic flux having the varying cross-sectional area is characterized by gradually-varying energy along the closed convergent-divergent tunnel-corridor, analogously to the property of the convergent-divergent electric flux described hereinabove in sub-paragraph “Venturi effect” with reference to prior art FIG. 1b, wherein the increased magnetic energy near the secondary electro-conductive-coil winding 5.93 is acquired from the electromagnetic gas temperature, hidden within the molecular ferromagnetic or ferrimagnetic material of the toroidal-like electro-conductive and magneto-boosting core 5.91.

(256) In contrast to the gauge transformer 5.8, where the current, induced in the secondary electro-conductive-coil winding 5.83, brings the electric power, equal to the electric power of the current flowing within the primary electro-conductive-coil winding 5.82, in the final analysis of the enhanced transformer 5.9, as an alternating magnetic flux of higher magnetic power induces a current bringing higher electric power, the current, induced in the secondary electro-conductive-coil winding 5.93, brings the electric power higher than the electric power of the current flowing within the primary electro-conductive-coil winding 5.92, wherein the added electric power is acquired at the expense of the electromagnetic gas temperature. The enhanced transformer 5.9 is interpreted as a motionless magnet-jet engine, allowing for a new beneficial capability of acquiring a useful electric energy from the electron gas temperature interrelated with the electromagnetic gas temperature, wherein: the primary (input) winding electro-conductive-coil 5.92 encircling the widened cross-section 5.95 plays the role of a magnetizing compressor, the vector angular-velocity, called also the angular-velocity-vector, of eddy currents (i.e. of circulating free electrons) plays the role of a molecular fluid flow velocity-vector, wherein streamlines of the induced eddy current are defined as curves aligned with the varying angular-velocity-vectors of the induced eddy current (or of the circular motion of the free electrons), being varying along the magnetic field strength force-lines 5.94 within and along the convergent-divergent electro-conductive and magneto-boosting core 5.91, and, looking ahead, the equation (6.13) described hereinbelow in subparagraph “Convergent-Divergent Jet-Nozzle” with reference to FIG. 6a, in particular, assuming Venturi M-velocities (where the term “Venturi M-velocity” will be introduced), is applicable to design an elaborated shape of actually-airfoil convergent-divergent tunnel-corridor of toroidal-like electro-conductive and magneto-boosting core 5.91, to provide: the required laminarity of magnetic flux 5.94 interrelated with eddy currents, and the desired gradual increase of the vector angular-velocity of the eddy currents.

(257) In view of the foregoing description of the subparagraph “Enhanced Transformer” referring to FIG. 5o, it will be evident for a person studied the present invention that one can use a multi-stage repeating cascade of a set of N enhanced transformers 5.9, wherein the primary (input) winding of each next enhanced transformer is electrically connected to the secondary (output) winding of the previous enhanced transformer. When each of the N enhanced transformers provides an increase in electric power due to the acquiring a useful electric energy from the ambient warmth by the factor F, the cumulative increase in the electric power becomes by the factor F.sup.N (for instance, F=1.1, N=10, and F.sup.N≈2.6).

(258) Permanent Electro-Magnet

(259) Referring again to FIG. 5o, the inventor further notes that considering the case: when the primary electro-conductive-coil windings: 5.82 and 5.92, each carrying a certain constant (not-alternating) current; and when the fragments: 5.87 and 5.97, are withdrawn, i.e. when the former closed toroidal-like cores: symmetrical equi-cross-sectional 5.81 and asymmetrical convergent-divergent 5.91, correspondingly, thereby become broken;
the transformers: 5.8 and 5.9, having the broken cores: 5.81 and 5.91, correspondingly, become functioning as permanent electro-magnets. It is expected that the magnetic field strength H.sub.5.87 in the gap 5.87 is weaker than the magnetic field strength H.sub.5.97 in the gap 5.97, because the cross-section of gap 5.87 is wider than the cross-section of gap 5.97; this follows from the equation of continuity applied to the magnetic flux. In other words, the identical primary electro-conductive-coil windings: 5.82 and 5.92, encircling identical cross-sections and thereby playing the role of identical magnetizing compressors, result in different magnetic properties of the permanent electro-magnets, called magnet-jet engines: 5.8 and 5.9, wherein the difference in magnetic properties between the magnet-jet engines: 5.8 and 5.9, is determined by the difference in cross-sectional varying of the broken cores: 5.81 and 5.91. The magnetic strength difference (H.sub.5.97−H.sub.5.87), accompanied by the magnetic field energy difference, is acquired at the expense of the electron gas temperature, i.e., at the final analysis, at the expense of the ambient temperature.
Convergent-Divergent Jet-Nozzle

(260) FIG. 6a is a schematic illustration of a convergent-divergent jet-nozzle 610, pipe-section in a sagittal plane. Convergent-divergent jet-nozzle 610 is applied to accelerate a compressed and hot air stream, or more generally, a laminarly flowing compressed and hot compressible-expandable fluid 611. Convergent-divergent jet-nozzle 610 has the inner tunnel opposite walls shaped, for simplicity, axis-symmetrically around an imaginary sagittal x-axis 615, as a convergent funnel 612 having open inlet, narrow throat 613 comprising point 618 of the narrowest cross-section, and divergent exhaust tailpipe 614 having open outlet, constructed according to an exemplary embodiment of the present invention providing the improved de Laval jet-effect. For simplicity, compressed and hot fluid stream 611 has a uniform front at the inlet.

(261) For the purposes of the present patent application, the de Laval effect should be understood in a wide sense as comprising both: the de Laval jet-effect, defined as an effect of flow extra-acceleration, and the de Laval retarding-effect, defined as an effect of flow extra-slowing. Thus, the de Laval jet-effect is a particular case of the de Laval effect.

(262) The specifically shaped tunnel, comprising the three major successive constituents: convergent funnel 612 having an open inlet, narrow throat 613, and divergent exhaust tailpipe 614 having an open outlet, has no real separation features between the constituents. For the purposes of the present patent application, first, narrow throat 613 is specified as a fragment of the inner tunnel located between imaginary inlet 6131 and outlet 6132; and second, the term “principal interval” of the x-axis is introduced as corresponding to the interval occupied by the specifically shaped tunnel, called an adapted convergent-divergent tunnel, i.e. at least comprising narrow throat 613.

(263) Fluid stream 611 is subjected to the Coanda-effect, observed as aligning of fluid stream 611 with the curvature of specifically shaped walls of the inner tunnel. The Coanda-effect is defined by a non-zero partial pressure-c P.sub.c arising when the shape of a fluid portion is varying as the fluid portion moves along the shaped inner tunnel of convergent-divergent jet-nozzle 610. Looking ahead, point out that the specific shape of tunnel, constructed according to the principles of the present invention, prevents disturbances of the fluid motion. This stipulation corresponds to the case when the cumulative-inner-static-pressure P of streaming fluid 611 is varying gradually and the velocity of streaming fluid 611 is varying linearly as the fluid 611 moves within the shaped tunnel along imaginary sagittal x-axis 615.

(264) For simplicity, imaginary sagittal x-axis 615 is horizontal, i.e. moving fluid 611 does not change its effective height above the Earth's ocean surface level. Thus, equations (5.6) and (5.7) for a stationary laminar flow can be written as (6.1) and (6.2) correspondingly:
udu+dQ=0 Eq. (6.1),
uρA=C=Const Eq. (6.2),
where C is a constant associated with the considered fluid portion, and values A, u, and ρ are associated with the flow cross-section: A is the flow cross-section area, u is the flow velocity, and ρ is the fluid density. Introduce value of volume of unit mass v, defined as v=1/ρ.

(265) The fluid characteristic heat portion per unit mass is defined as Q=P/ρ=Pv, so dQ=vdP+Pdv, where P=P.sub.in=P.sub.s+P.sub.drag+P.sub.viscous Therefore, equation (6.1) can be represented as
udu+vdP+pdv=0 Eq. (6.3a).
Dividing (6.3a) by Pv, one obtains:

(266) $\begin{matrix} \frac{udu}{Pv} + \frac{dP}{P} + \frac{dv}{v} = 0, and so, & Eq . (6.3 b) \\ \frac{dv}{v} = - \frac{udu}{Pv} - \frac{dP}{P} . & Eq . (6.3) \end{matrix}$
Rewrite equation (6.2) as:
uA=Cv Eq. (6.4a).
and further in differential form as:
Adu+udA=Cdv Eq. (6.4b).
Divide the left and right sides of (6.4b) by the left and right sides of (6.4a) correspondingly:

(267) $\begin{matrix} \frac{du}{u} + \frac{dA}{A} = \frac{dv}{v} . & Eq . (6.4) \end{matrix}$
Referring to equation (5.8a) for a real molecular fluid undergoing a reversible adiabatic process, one can write: Pv.sup.γ=Const, or in differential form:
v.sup.γdP+γPv.sup.γ−1dv=0 Eq. (6.5a).
Dividing (6.5a) by γPv.sup.γ, one obtains:

(268) 0 $\begin{matrix} \frac{dv}{v} = - \frac{dP}{γ P} . & Eq . (6.5) \end{matrix}$
Comparing (6.5) and (6.3), one can write:

(269) $\begin{matrix} - \frac{udu}{Pv} - \frac{dP}{P} = - \frac{dP}{γ P}, i . e . & Eq . (6.6 a) \end{matrix}$ $\begin{matrix} - \frac{udu}{Pv} \frac{γ u}{γ u} = - \frac{dP}{γ P} + \frac{γ}{γ} \frac{dP}{P} . & Eq . (6.6 b) \end{matrix}$
The denominator of the left side of (6.6b) comprises value (γPv) that defines velocity of sound via equation u.sub.sound=√{square root over (γPv)}, so (6.6b) can be rewritten as:

(270) $\begin{matrix} - \frac{γ u^{2}}{u_{sound}^{2}} \frac{du}{u} = \frac{γ - 1}{γ} \frac{dP}{P} . & Eq . (6.6 c) \end{matrix}$
Introducing the value M=u/u.sub.sound having the meaning of the fluid portion velocity measured in Mach numbers, i.e. M-velocity, (6.6c) can be written as:

(271) $\begin{matrix} - γ M^{2} \frac{du}{u} = \frac{(γ - 1)}{γ} \frac{dP}{P} . & Eq . (6.6) \end{matrix}$
Now comparing (6.5) and (6.4), one gets:

(272) $\begin{matrix} \frac{dP}{γ P} = - \frac{dA}{A} - \frac{du}{u} . & Eq . (6.7) \end{matrix}$
Substituting the expression for dP/γP from (6.7) into (6.6), one obtains:

(273) $- γ M^{2} \frac{du}{u} = (γ - 1) (- \frac{dA}{A} - \frac{du}{u})$
and after simple algebraic transformations one formulates:

(274) $\begin{matrix} \frac{dA}{A} = (\frac{γ}{γ - 1} M^{2} - 1) \frac{du}{u} . & Eq . (6.8) \end{matrix}$
Equation (6.8) comprises the term M.sup.2γ/(γ−1) characterizing the effect of the gas compressibility and expandability. Equation (6.8) differs from classical equation (1b) derived from the Euler equations applied to an ideal fluid defined in frames of the continuum mechanics. In particular, equation (6.8) says that: if the horizontally moving flow is relatively slow (i.e. M<√{square root over ((γ−1)/γ))}, then the narrowing of the flow cross-section (i.e. negative dA) corresponds to acceleration of the flow (i.e. positive du); and if the flow is relatively fast (i.e. M>√{square root over ((γ−1)/γ))}, then just the widening of the flow cross-section (i.e. positive dA) corresponds to acceleration of the flow (i.e. positive du). This means, in particular, that at so-called “critical condition” point 680 defined for the narrowest throat of the de Laval nozzle, the flow specific M-velocity equals
M.sub.*=√{square root over ((γ−1)/γ)} Eq. (6.9).

(275) For the purposes of the present patent application, here and further, the lower index “*” is applied to an M-velocity, geometrical and thermodynamic parameters in a critical condition point.

(276) For air as a diatomic molecular gas, the generalized adiabatic compressibility parameter γ equals γ=7/5=1.4, and M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach, but not 1 Mach as follows from classical equation (1b). For a gas composed of multi-atomic molecules, the generalized adiabatic compressibility parameter γ is closer to 1, and so the de Laval jet-effect is expected at lower M-velocities. In a particular case of an almost incompressible liquid, the generalized adiabatic compressibility parameter γ is extremely great and equation (6.8) comes close to classical equation (1b), for which M.sub.*=1 Mach.

(277) In many actual and imaginary applications the phenomenon of shock sound-wave emission, that arises at M-velocities near 1 Mach, is undesirable or unacceptable. Therefore, the conclusion of resulting equation (6.8), that the de Laval jet-effect begins from the velocity being substantially lower than the speed of sound, becomes important to provide for a utilization of this useful effect avoiding the phenomenon of shock sound-wave emission.

(278) Now consider the case where a compressed and/or heated gas, defined by the stagnation parameters: pressure P.sub.0, density ρ.sub.0, and temperature T.sub.0, is launching into a convergent-divergent jet-nozzle. Let the stagnation pressure P.sub.0, temperature T.sub.0, and density ρ.sub.0 be much high to provide the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the narrowest cross-section of the throat. The gas characteristic heat portion per unit mass, expressed in terms of the gas temperature, is: Q=RT. Substitution of this expression into (6.1) gives:

(279) $\begin{matrix} T_{0} = T + \frac{u^{2}}{2 R} = T (1 + M^{2} \frac{γ}{2}) & Eq . (6.1) \end{matrix}$
where T.sub.0 is the stagnation temperature; T is the gas portion current temperature; u.sub.sound=√{square root over (γPv)}=√{square root over (γRT)}, and M=u/u.sub.sound=u/√{square root over (γRT)}. Though the normalized value M depends on temperature, one retains the form of equation (6.10) expressed via M, because the value of M=1 Mach has the physical sense of the shock sound-wave emission condition. Taking into account relations between thermodynamic parameters in an adiabatic process, equation (6.10) can be rewritten as:

(280) $\begin{matrix} \frac{T_{0}}{T} = {(\frac{P_{0}}{P})}^{\frac{γ - 1}{γ}} = {(\frac{ρ_{0}}{ρ})}^{γ - 1} = 1 + M^{2} \frac{γ}{2} & Eq . (6.11) \end{matrix}$
where P and ρ are the current static pressure and density correspondingly.

(281) It is important to introduce the ratio A/A.sub.*, where A.sub.* is the narrowest cross-sectional area of the nozzle throat, i.e. is the critical condition area corresponding to the critical condition point, and A is the current cross-sectional area. It follows from (6.2) that

(282) $\begin{matrix} \frac{A}{A_{*}} = \frac{ρ_{*}}{ρ} \frac{u_{*}}{u} & Eq . (6.12) \end{matrix}$
Taking into account (6.11) and that the specific M-velocity equals M.sub.*=√{square root over ((γ−1)/γ)}, the ratio A/A.sub.* can be expressed via M-velocity:

(283) 0 $\begin{matrix} \frac{A}{A_{*}} = \frac{1}{M} {(\frac{γ - 1}{γ})}^{\frac{1}{2}} {(\frac{2 + γ M^{2}}{γ + 1})}^{\frac{γ + 1}{2 (γ - 1)}} & Eq . (6.13) \end{matrix}$

(284) Equation (6.13) derived from the equation of continuity for an adiabatic process is the equation of M-velocity, bonding the generalized adiabatic compressibility parameter γ, M-velocity M, and ratio A/A.sub.* of the molecular fluid, fast and laminarly flowing through the de Laval nozzle, oriented horizontally. Equation (6.13) differs from classical equation (1) derived basing on the Euler equations applied to an ideal fluid defined in frames of the continuum mechanics. Equation (6.13), as one of the primary teachings of the present invention, says that to accelerate a warmed and compressed air portion up to 1 Mach, one must apply a convergent-divergent jet-nozzle and provide the nozzle inner tunnel divergent part expansion up to the ratio of A/A.sub.*≈1.5197. Considering an essential M-velocity range, specified as an M-velocity range comprising M-velocities corresponding to the flow passing through the principal interval, equation (6.13) can be applied to make an ideal shape of the nozzle to provide for a laminar motion and thereby optimize the acceleration of the streaming fluid at least in the essential M-velocity range, i.e. at least within the specifically shaped tunnel. In contrast to the prior art concept of rapid expansion and acceleration of the gas, described hereinbefore with reference to FIGS. 1c and 1d, that causes the arising of undesired Mach waves, the substantially gradual (or linear) increase of the M-velocity downstream along the gas motion accompanied by the interrelated gradual (or linear) change of fluid thermodynamic parameters, is a criterion of the nozzle inner tunnel shape optimization preventing turbulences and, in particular, providing suppression of the undesired Mach waves, according to an exemplary embodiment of the present invention.

(285) Further, for the purposes of the present patent application, use of the equation of M-velocity (6.13) assumes an inherent condition of a gradual change of the fluid thermodynamic parameters. So, axis-symmetrical convergent-divergent jet-nozzle 610, comprising specifically shaped convergent funnel 612 having an open inlet, narrow throat 613, and divergent exhaust tailpipe 614 having an open outlet, is designed according to equation (6.13), where the value M corresponds to x-coordinates along imaginary x-axis 615 as a smooth function M(x). In particular, a linear function M(x) was chosen as a desired for M(x), i.e. M(x)=M(x)=M.sub.*+α.sub.M(x−x.sub.*), where x is the x-coordinate at x-axis 615, and α.sub.M is a positive constant defining a scale factor and having a sense of constant gradient of M-velocity spatial distribution, i.e. a.sub.M=∂M(x)/∂x. Such a relationship enables a substantially smoothed increase of M-velocity as the fluid moves through the specifically shaped tunnel of convergent-divergent jet-nozzle 610. The linear increase of M-velocity prevents substantially the arising of streaming fluid 611 motion disturbances, accompanied by shock waves.

(286) In contrast to a jump-like sharp slope, the gradual change of the M-velocity and so of all the interrelated thermodynamic parameters is one of the primary features of the de Laval jet-effect improvement.

(287) For the purposes of the present patent application, the term “de Laval enhanced jet-effect” or briefly: “enhanced jet-effect” is introduced as relating to the modified de Laval jet-effect, occurring in a convergent-divergent tunnel having a specifically revised shape according to the principles of the present invention, such that the modified de Laval jet-effect becomes improved by smoothing of the fluid thermodynamic parameters spatial distribution, providing the following beneficial features: smoothing of the flowing fluid M-velocity, providing suppression of the undesired flow disturbances accompanied by shock waves; smoothing of the flowing fluid static pressure, providing suppression of the undesired Mach waves and, thereby, suppression of nearby body vibrations; smoothing of the flowing fluid temperature, providing suppression of adjacent surface tensions; and smoothing of the flowing fluid density, providing suppression of shock waves.
Also, the term “de Laval-like jet-effect” should be understood in a wider, sense including a case when an enhanced jet-effect occurs in an open space imaginably bordered by the flow streamlines, wherein the imaginary borders constitute a convergent-divergent shape, i.e. similar to a de Laval nozzle.

(288) If the exhaust tailpipe 614's outlet area is A.sub.e, the ratio A.sub.e/A.sub.* defines the nozzle expansion ratio that can be optimized in accordance with the estimations described hereinbelow with reference to FIGS. 7a, 7b, 7c. Thereby, a convergent-divergent jet-nozzle, constructed applying equation (6.13) according to an exemplary embodiment of the present invention, allows a use of the de Laval enhanced jet-effect to accelerate incoming compressed and hot airstream 611 moving with low M-velocities to obtain oufflowing accelerated and cooled jetstream 616, reaching high M-velocities [i.e. M-velocities, higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}], in particular, high-subsonic velocities.

(289) FIG. 6b, in conjunction with FIG. 6a, is a schematic graphic illustration of the distribution of the flowing fluid 611's three parameters: velocity 620, static pressure 630, and temperature 640 along the length of nozzle 610, constructed according to the principles of a preferred embodiment of the present invention. The narrowest cross-section of the throat 613 (FIG. 6a) provides the “critical condition” point 618. Compressed and hot fluid 611 flows through throat 613, where the velocity picks up 621 such that M-velocity reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} 623 at the critical condition point 618. Ahead of the critical condition point 618, the pressure and temperature fall, correspondingly 631 and 641. Hot flowing fluid 611 crosses the critical condition point 618 and enters the widening stage of throat 613 and further divergent exhaust tailpipe 614 having an open outlet. Flowing fluid 611 expands there, and this expansion is optimized such that the extra-increase of M-velocity 622 is substantially smoothed; and the pressure and temperature extra-decrease, 632 and 642, correspondingly, are substantially smoothed as well, in contrast to that at the critical condition point 180 with reference to the classic prior art rocket nozzle 100 of FIGS. 1c, 1d. The smoothed change of static pressure 630 provides a suppression of unwanted Mach waves. In practice, the suppression of Mach waves provides a suppression of undesired vibrations that, in particular, especially important for fast accelerating vehicles.

(290) In view of the foregoing description referring to FIG. 6a, it will be evident to a person skilled in the art that one can use different criteria of gradualness of M(x) for different preferred optimizations of the convergent-divergent shape of a tunnel. Namely, the conditions, providing laminarity of the airstream motion, are: if suppression of Mach waves and of body vibrations are the most preferable, then M(x) should be given as the function

(291) $M (x) = \sqrt{2 {{[P_{0} / \overline{P} (x)]}^{(γ - 1) / γ} - 1} / γ},$ where P(x) is a linear function of the static pressure vs. x-coordinate: P(x)=P.sub.*+α.sub.P(x−x.sub.*), P.sub.* is the static pressure of the flowing fluid at the critical condition point x.sub.*, and α.sub.P=∂P(x)/∂x is a constant gradient of the static pressure distributed along the x-axis within a specially shaped tunnel; and FIG. 6c is a schematic illustration of an exemplary profile of an optimized specifically shaped tunnel providing a linear change of the flowing fluid static pressure corresponding to the essential M-velocity range comprising M-velocities from 0.02 up to 2 Mach; if the suppression of temperature jumps is the most preferable, then M(x) should be given as the function

(292) $M (x) = \sqrt{2 {[T_{0} / \overline{T} (x)] - 1} / γ},$ where T(x) is a linear function of the fluid temperature vs. x-coordinate: T(x)=T.sub.*+α.sub.T(x−x.sub.*), T.sub.* is the temperature of the flowing fluid at the critical condition point x.sub.*, and α.sub.T=∂T(x)/∂x is a constant gradient of the fluid temperature distributed along the x-axis within a specially shaped tunnel; and FIG. 6d is a schematic illustration of an exemplary profile of an optimized specifically shaped tunnel providing a linear change of the flowing fluid temperature corresponding to the essential M-velocity range comprising M-velocities from 0.02 up to 2 Mach; and if a trade-off between suppressions of Mach waves and temperature jumps is preferable, then M(x) should be given as the function

(293) $M (x) = \sqrt{2 {{[ρ_{0} / \overline{ρ} (x)]}^{(γ - 1)} - 1} / γ},$ where M(x) is a linear function of the fluid density vs. x-coordinate: ρ(x)=ρ.sub.*+α.sub.ρ(x−x.sub.*), ρ.sub.* is the density of said flowing fluid at the critical condition point x.sub.*, and α.sub.β=∂ρ(x)/∂x is a constant gradient of the fluid density distributed along the x-axis within a specially shaped tunnel; and FIG. 6e is a schematic illustration of an exemplary profile of an optimized specifically shaped tunnel providing a linear change of the flowing fluid density corresponding to the essential M-velocity range comprising M-velocities from 0.02 up to 2 Mach.

(294) Further, for the purposes of the present invention, the term “airfoil” or “actually-airfoil” should be understood as related to a wall shape and as specifying a convergent-divergent shape of a flow portion's streamlines aligned to the airfoil wall, wherein, in contrast to a seemingly-airfoil shape, the convergent-divergent shape calls for the differential equation of motion (6.8), equation of M-velocity (6.13), and at least one of the aforementioned conditions for the function M(x), thereby providing laminarity of the flow portion motion.

(295) Furthermore, it will be evident to a person skilled in the art that:

(296) One can optimize the specifically shaped tunnel of convergent-divergent jet-nozzle 610 providing such conformity of the cross-sectional area of the open inlet with the M-velocity of flowing fluid crossing the open inlet, that the flowing fluid M-velocity is substantially smooth at the entering the open inlet. Moreover, one can control the cross-sectional area of the open inlet, according to the equation of M-velocity, providing conformity of the open inlet cross-sectional area with the variable M-velocity of the entering flowing fluid afore-and-nearby the open inlet. This may become important, for example, to suppress vibrations of a fast accelerating vehicle; and As soon as the de Laval effect occurs in an adiabatic process, the condition of fluid stream 611 motion through the narrowest cross-section of throat 613 at critical condition point 618 with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} 623, accompanied by thermodynamic parameters: static pressure P.sub.*, temperature T.sub.*, and fluid density ρ.sub.*, interrelates with a condition of fluid stream 611 motion with an M-velocity and accompanied thermodynamic parameters static pressure P, temperature T, and fluid density ρ at any cross-section of convergent-divergent jet-nozzle 610's inner tunnel, wherein the conditions interrelation depends on the tunnel geometry only. In other words, if a hypothetical ideal propeller pushing a hypothetic inviscid fluid provides the inviscid fluid laminar flow with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the critical condition point of a de Laval nozzle, then the de Laval effect becomes triggered in the de Laval nozzle of a fanjet engine, wherein the thermodynamic parameters of the moving inviscid fluid portions are interrelated as in an adiabatic process. In this case, the hypothetical propeller triggering the de Laval effect expends power for the launching of accompanying shock and/or Mach waves only.
In view of the foregoing description referring to FIG. 6a, it will be also evident to a person skilled in the art that: In a more general case, when imaginary sagittal axis 615 is oriented at least partially in the vertical direction in the Earth's gravitational field, the equation of M-velocity should be corrected becoming different from equation (6.13) by a component depending on the gravitational acceleration g, namely:

(297) $\begin{matrix} \frac{A}{A_{*}} = \frac{M_{*}}{M} {(\frac{1 + \frac{γ}{2} M^{2} + \frac{g Δ h}{RT}}{1 + \frac{γ}{2} M_{*}^{2}})}^{\frac{γ + 1}{2 (γ - 1)}}, & Eq . (6.14) \end{matrix}$ where Δh is a change of the flow effective height with respect to the critical condition point. It will be further evident to a person skilled in the art that, when the considered temperatures and M-velocities are sufficiently high to provide for the conditions: gΔh/RT<<1 and gΔh/RT<<γM.sup.2/2 to be satisfied, a use of the equation of M-velocity in the form of equation (6.13) becomes justified; Taking into account molecular interactions for flowing liquid or plasma, for which changes of the partial deep-stagnation pressure-a δP.sub.a become at least noticeably distributed in space, the generalized adiabatic compressibility parameter γ in the equation of M-velocity (6.13) is not a constant, but varies with the changes of the partial deep-stagnation pressure-a δP.sub.a, in a conformance with equations (5.8b) and (5.8c); If the flowing molecular fluid is an ionized gas, i.e. plasma, controlled by an external magnetic field, then the specifically shaped walls of tunnel can be imaginary, formed by streamlines of the flowing plasma subjected to and controlled by an action of the magnetic field; and According to the kinetic theory of matter, a substantial incompressible molecular fluid, characterized by almost not changeable thermodynamic parameters: density, temperature, and inner-static-pressure and characterized by the infinitely great generalized adiabatic compressibility parameter γ.fwdarw.∞, cannot change its cross-sectional area substantially, and so, according to equation of M-velocity (6.13), cannot flow laminarly through a horizontal tunnel having a varying cross-sectional area; and furthermore, strictly speaking, a hypothetical absolutely-incompressible molecular fluid cannot flow through a converging tunnel at all. This is a theoretically important teaching of the present invention.
De Laval Retarding-Effect

(298) FIG. 6f is a schematic illustration of an inverse convergent-divergent jet-nozzle 650, pipe-section in a sagittal plane. Convergent-divergent jet-nozzle 650, constructed according to the principles of a preferred embodiment of the present invention, as inverse de Laval nozzle, applied to retard a fast fluid-flow 651, streaming with a high M-velocity M.sub.651, higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. Convergent-divergent jet-nozzle 650 has the sectional shape mirror-symmetrically congruent to the sectional shape of convergent-divergent jet-nozzle 610, shown in FIG. 6a, and oriented to oncoming fluid-flow 651 in the back direction. Namely, the shape is axis-symmetrical around an imaginary sagittal axis 655; convergent funnel 652 having open inlet is as inverse divergent exhaust tailpipe 614; narrow throat 653 comprises point 658 of the narrowest cross-section; and divergent exhaust tailpipe 654 is as inverse convergent funnel 612. Convergent funnel 652, narrow throat 653, and divergent exhaust tailpipe 654 have not real separation features between them. For the purpose of the present patent application narrow throat 653 is specified as a fragment of the inner tunnel having imaginary inlet 6531 and outlet 6532, wherein the term “principal interval” of x-axis has a sense as corresponding to the interval occupied by the specifically shaped tunnel, i.e. at least comprising narrow throat 653.

(299) FIG. 6g, in conjunction with FIG. 6f, is a schematic graphic illustration of the distribution of the fluid 651's three parameters: velocity 660, static pressure 670, and temperature 680 along the length of nozzle 650 calculated according to equations (6.11) and (6.13).

(300) The narrowest cross-section of the throat 653 (FIG. 6f) provides the “critical condition” point 658, triggering the inverse de Laval jet-effect, according to equation (6.13), that is observed as an effect of flow slowing, when the flow moves along convergent funnel 652, and further slowing, when the flow moves through the divergent stage of convergent-divergent jet-nozzle 650 downstream-behind the critical condition point 658. For the purposes of the present patent application, the term “de Laval retarding-effect” is introduced as relating to the inverse de Laval jet-effect. Fast fluid-flow 651 moves along convergent funnel 652, where, ahead of the critical condition point 658 of narrow throat 653, the velocity falls 661, and the pressure and temperature pick up, correspondingly 671 and 681. The velocity falls 661 such that M-velocity M.sub.663, corresponding to marker 663, reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the critical condition point 658. Fluid-flow 651 exits throat 653 and enters the widening divergent exhaust tailpipe 654, where fluid-flow 651 is subjected to increase of cross-sectional area, and this action is optimized such that the decrease of M-velocity 662 is accompanied by a substantially smoothed increase of the pressure and temperature, 672 and 682, correspondingly. Slow hot and compressed fluid at position 656 outflows from wide exhaust tailpipe 654. Again, the smoothed change of static pressure 670 provides a suppression of unwanted Mach waves. In practice, the suppression of Mach waves provides a suppression of undesired vibrations that, in particular, especially important for a fast decelerating flying vehicle.

(301) In view of the foregoing description referring to FIGS. 6f and 6g, it will be evident to a person skilled in the art that, on the one hand, to trigger the de Laval retarding-effect the high M-velocity M.sub.651 must be low sufficient to reach the specific M-velocity M.sub.* while slowing in convergent funnel 652 and the convergent stage of throat 653. On the other hand, taking into account that, in practice, for the case wherein fluid-flow 651 is an airflow, the M-velocity is distributed in the direction normal to an adjacent surface such that decreases almost down to zero at the surfaces of convergent-divergent jet-nozzle 650's walls. Thus, a certain portion of fast fluid-flow 651 at the critical condition point 658 moves with the effective M-velocity equal to the specific M-velocity M.sub.* and is subjected to a convergent-divergent reshaping in throat 653, thereby, the conditions for the de Laval retarding-effect triggering is satisfied for any high M-velocity M.sub.651, higher than the specific M-velocity M.sub.*.

(302) In view of the foregoing description referring to FIGS. 6a, 6b, 6f and 6g and derivation of equations (6.8) and (6.9), the de Laval jet-effect and the de Laval retarding-effect, both observed in the case of a converging flow, are specified as the following. The de Laval jet-effect is specified as an effect of a convergent flow portion convective acceleration, occurring, when the convergent flow portion moves with M-velocities lower than the specific M-velocity upstream-afore the critical condition point, reaches the specific M-velocity at the critical condition point, and moves with M-velocities higher than the specific M-velocity downstream-behind the critical condition point; and the de Laval retarding-effect is specified as an effect of a convergent flow portion warming and slowing, occurring, when the convergent flow portion moves with M-velocities higher than the specific M-velocity upstream-afore the critical condition point, reaches the specific M-velocity at the critical condition point, and moves with M-velocities lower than the specific M-velocity downstream-behind the critical condition point.

(303) For the purposes of the present patent application, the terms “Venturi M-velocity”, “de Laval M-velocity”, “de Laval low M-velocity”, and “de Laval high M-velocity” should be understood as the following: a Venturi M-velocity is defined as an M-velocity, lower than the specific M-velocity M.sub.* and low sufficient to cross a narrow throat with said M-velocity, lower than the specific M-velocity M.sub.*; a de Laval low M-velocity is defined as an M-velocity lower than the specific M-velocity M.sub.* and high sufficient to reach the specific M-velocity M.sub.* at the critical condition point x.sub.*; a de Laval high M-velocity is defined as an M-velocity higher than the specific M-velocity M.sub.* and low sufficient to reach the specific M-velocity M.sub.* at the critical condition point x.sub.*; and a de Laval M-velocity is at least one of the de Laval low M-velocity and the de Laval high M-velocity.

(304) In view of the foregoing description referring to FIGS. 6f and 6g, it will be evident to a person skilled in the art that one can optimize the specifically shaped tunnel of convergent-divergent jet-nozzle 650 providing such a conformity of the cross-sectional area of the open inlet with the de Laval high M-velocity of flowing fluid crossing the open inlet, that the flowing fluid M-velocity is substantially smooth at the entering the open inlet. Furthermore, one can control the cross-sectional area of open inlet, according to the equation of M-velocity, providing conformity of the open inlet cross-sectional area with the variable M-velocity of the entering flowing fluid. This may become important, for example, to suppress vibrations of a fast slowing vehicle.

(305) Two-Stage Convergent-Divergent Jet-Nozzle

(306) FIG. 6h is a schematic illustration of a two-stage convergent-divergent jet-nozzle 690 exposed to an incoming fast fluid-flow 691, streaming with a high M-velocity M.sub.691, higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, i.e. with a de Laval high M-velocity. Two-stage convergent-divergent jet-nozzle 690, constructed according to the principles of a preferred embodiment of the present invention, has an inner tunnel comprising the first and second convergent-divergent stages, separated by widened reservoir 694. The first convergent-divergent stage performs the first-stage convergent inlet-funnel 692 gradually turning into the first-stage narrow convergent-divergent throat 693 having a local narrowest cross-section providing the first critical condition point 6981 and having an inverse-funnel shaped pipe leading to widened reservoir 694. The second convergent-divergent stage comprises the second-stage narrow throat 696, having a local narrowest cross-section providing the second critical condition point 6982, and the second-stage divergent exhaust tailpipe 697.

(307) Incoming fast fluid-flow 691 is gradually slowing down, becoming warmer and more thickened and compressed as moving along the first convergent-divergent stage to widened reservoir 694 as described hereinbefore with reference to FIGS. 6f and 6g. Slow, hot and compressed fluid 695 further movies through the second convergent-divergent stage. The fluid flow is accelerating as moving through throat 696, where exceeds the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} downstream-behind the second critical condition point 6982. Jetstream 699 outflowing through divergent exhaust tailpipe 697, is faster and colder than slow, hot and compressed fluid 695, yet to be entered into the second convergent-divergent stage, as described hereinbefore tracing after incoming compressed and hot airstream 611 with reference to FIGS. 6a and 6b. Fast outflowing jetstream 699 has a cross-section wider than incoming fast fluid-flow 691 at the input of convergent inlet-funnel 692. So, the M-velocity M.sub.699 of fast outflowing jetstream 699 is higher than the M-velocity M.sub.691 of fast fluid-flow 691, according to equation (6.13).

(308) Thereby, two-stage convergent-divergent jet-nozzle 690 operates as a jet-booster based on the de Laval enhanced jet-effect launching outflowing jetstream 699, which is faster than fast fluid-flow 691 incoming with the de Laval high M-velocity M.sub.691, i.e. higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. This is one more teaching of the present invention.

(309) Optimal Implementation of Convergent-Divergent Jet-Nozzle

(310) FIG. 7a shows comparative graphs 700 for the dependencies of the nozzle tunnel extension ratio vs. the airflow M-velocity, calculated by the classical and suggested models, namely, curves 703 and 704 correspondingly; wherein the vertical axis 701 is the ratio A/A.sub.*, and the horizontal axis 702 is the airflow M-velocity measured in temperature dependent Mach numbers. The dashed curve 703 is the convergent-divergent cross-sectional area ratio A/A.sub.* profile vs. the airflow M-velocity, calculated using equation (1) derived from the Euler equations of fluid motion. The solid curve 704 is the convergent-divergent cross-sectional area ratio A/A.sub.* profile vs. the airflow M-velocity, calculated using the suggested equation (6.13) derived from the generalized equations of fluid motion. The critical condition point 708 corresponds to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345. Comparative graphs 700 show that one needs in a substantially extra-widened nozzle tunnel 704 to reach the airflow M-velocities substantially higher than 1 Mach.

(311) Therefore, a convergent-divergent jet-nozzle, constructed according to an exemplary embodiment of the present invention, allows increased efficiency of the jet-effect for use at high-subsonic, transonic, supersonic, and hypersonic velocities that can be applied to rocket nozzle design.

(312) Taking into account relation (6.11), one can derive equations bonding the exhaust-nozzle outlet M-velocity M.sub.e with the ratios P.sub.0/P.sub.e and T.sub.0/T.sub.e, where P.sub.e and T.sub.e are correspondingly the static pressure and temperature at the exhaust-nozzle tunnel outlet:

(313) $\begin{matrix} M_{e} = \sqrt{\frac{2}{γ}} \sqrt{{(\frac{P_{0}}{P_{e}})}^{\frac{γ - 1}{γ}} - 1} & Eq . (7.1 a) \\ \frac{P_{0}}{P_{e}} = {(\frac{2 + γ M_{e}^{2}}{2})}^{\frac{γ}{γ - 1}} & Eq . (7.1 b) \\ \frac{T_{0}}{T_{e}} = (\frac{2 + γ M_{e}^{2}}{2}) & Eq . (7.1 c) \\ \frac{ρ_{0}}{ρ_{e}} = {(\frac{2 + γ M_{e}^{2}}{2})}^{\frac{1}{γ - 1}} & Eq . (7.1 d) \end{matrix}$

(314) In contrast to the classical theory, saying that both: the de Laval jet-effect and the velocity of sound are reachable when the ratio P.sub.0/P.sub.e is of 1.893, equation (7.1b) shows that, on the one hand, to obtain the de Laval jet-effect [i.e. condition M.sub.e≥M.sub.*] for air using a nozzle tunnel having an optimal convergent-divergent shape, one must provide the ratio P.sub.0/P.sub.* at least of 1.893, and, on the other hand, to accelerate an air portion up to the velocity of sound [i.e. M.sub.e=1], one must provide the ratio P.sub.0/P.sub.e at least of 6.406. Equation (7.1c) says that, on the one hand, to obtain the de Laval jet-effect for air utilizing a nozzle tunnel having optimal convergent-divergent shape, one must provide the ratio T.sub.0/T.sub.* at least of 1.2; and, on the other hand, to accelerate an air portion up to the velocity of sound, one must provide the ratio T.sub.0/T.sub.e at least of 1.7. So, the principle condition either 1.893<P.sub.0/P.sub.e<6.406 or/and 1.2<T.sub.0/T.sub.e<1.7 may provide the de Laval jet-effect occurring without the phenomenon of shock sound-wave emission that is one of the primary principles of the present invention.

(315) Thus, a convergent-divergent jet-nozzle tunnel, constructed according to an exemplary embodiment of the present invention and exploited in accordance with the principle conditions, allows an optimal implementation and efficient use of an enhanced jet-effect at de Laval M-velocities.

(316) Vortex Tube as Convergent-Divergent Jet-Nozzle

(317) Reference is now made again to prior art FIG. 1l, showing vortex-tube 190, and FIG. 6a, showing convergent-divergent jet-nozzle 610 constructed according to an exemplary embodiment of the present invention.

(318) Point out that the vortex tube 190's exhaust tunnels to outlets 317 and 318 can be considered as converging and convergent-divergent jet-nozzles correspondingly at heating and cooling ends. Consider, for simplicity, the nozzle effect only at outlet 19.8. Apply estimations (7.1a,b,c) to an ideal construction of vortex tube 190 and take into account the aforementioned conditions of exploitation. Namely, entering air 310 has the pressure of P.sub.0=6.9 bar, while the value P.sub.e is about 1 bar such that P.sub.0/P.sub.e is substantially higher than 1.893 that provides M-velocity of M.sub.*=√{square root over ((γ−1)/γ)} into the “throat” 19.9. Moreover, the estimated ratio P.sub.0/P.sub.e˜6.4 says that if the widening exhaust tunnel, having outlet 19.8 diameter greater than inner diameter 19.9 would be constructed in accordance with an exemplary embodiment of the present invention similar to convergent-divergent jet-nozzle 610 (FIG. 6a) such that A.sub.e/A.sub.*≈1.5197, then outlet 19.8 M-velocity is expected to be approximately of M.sub.e≈1. In this case, it follows from (7.1c) that the reachable temperature ratio is T.sub.0/T.sub.e=1.7. I.e., if T.sub.0=21° C.=294.14° K, then T.sub.e≈173° K≈−100° C. This estimation shows that: first, the novel explanation of the well-known vortex-tube effect by the dominant phenomenon occurred in the de Laval convergent-divergent jet-nozzle is confirmed by calculations based on equations (7.1a,b,c); and second, a cooling temperature, substantially lower than the aforementioned “−34° C.”, is reachable by optimizing the mentioned outlet convergent-divergent tunnel shape.

(319) Thus, a convergent-divergent jet-nozzle, constructed and exploited according to an exemplary embodiment of the present invention, allows optimizing the efficiency of an enhanced jet-effect use to launch an extra-cooled gas outflow.

(320) Compressor Supplied by Convergent-Divergent Jet-Nozzle

(321) FIG. 7b is a schematic illustration of a hypothetically optimal convergent-divergent jet-nozzle 710 with the critical condition point 718 applied to accelerate air portion 711, constructed according to the principles of the present invention. Air portion 711 is compressed and heated in a reservoir 712. To compress air portion 711 up to pressure P.sub.0=6.4 bar one needs to consume the energy E.sub.0 estimated as (P.sub.0−P.sub.e)V.sub.0, where V.sub.0 is the volume of the gas reservoir 712. For V.sub.0=1 m.sup.3, the energy E.sub.0 is estimated as E.sub.0≈5.4×10.sup.5 J=540 kJ. The volume V.sub.0 is composed of approximately n (P.sub.0/P.sub.e)×1000/22.4=286 moles of gas. When air portion 711 is accelerated and expanded in de Laval-like nozzle 710, it acquires kinetic energy at the expense of thermodynamically related pressure and temperature decrease; wherein the pressure decreases from P.sub.0 to P.sub.e and the temperature decreases from T.sub.0 to T.sub.e. Let air portion 711 accelerate in hypothetically optimal convergent-divergent jet-nozzle 710 such that the velocity of the outflowing stream 713 is almost as the speed of sound, i.e. the exhaust M-velocity is of M.sub.e≈1. Then T.sub.0/T.sub.e=1.7 and (T.sub.0−T.sub.e)=T.sub.0(1-1/1.7)=0.412T.sub.0. In this case, the acquired kinetic energy equals K=n×(T.sub.0−T.sub.e)R that is estimated as:
K=n×0.412T.sub.0R≈286×0.412×298×278≈9,761,674 J=9,762 kJ.

(322) This estimation shows that the triggered acquired kinetic energy K may exceed the triggering consumed energy E.sub.0 at least at subsonic velocities by the factor of 18 times. The acquired kinetic energy can be applied to a vehicle motion or to an engine for electricity generation with positive net-efficiency. On the other hand, the acquiring of kinetic energy is accompanied by the air temperature decrease, therefore, such a convergent-divergent jet-nozzle can be applied to cooling of a vehicle engine as well as be used either for electricity harvesting by means of a Peltier element operating as thermoelectric generator and/or as an effective condenser of vapor to water.

(323) Flying Capsule as Dragging-Jet Engine

(324) FIG. 7c is a schematic sectional view of a flying capsule corpus 720 in a sagittal plane. Capsule corpus 720, constructed according to the principles of the present invention, has outer airfoil side 729 and comprises an inner converging reservoir 721 as a dragging compressor having an open inlet 725 exposed to ambient wind 724 and further having a hypothetically optimal convergent-divergent tunnel 722 with a narrow throat comprising a critical condition point 728 and divergent exhaust tailpipe having an open outlet 726 of area A.sub.e. The velocity of ambient air 724 relative to capsule 720 is u.sub.a which is substantially lower than the critical condition velocity u.sub.*, corresponded to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. The wind portion 727 enters the inner converging reservoir 721 with the velocity equal to u.sub.in. The area A.sub.in of inlet 725 is substantially wider than the area A.sub.* of the throat's cross-section at the critical condition point 728 such that air portion 727 crosses the area A.sub.* at the critical condition point 728 with the maximal reachable M-velocity equal to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, and so the de Laval enhanced jet-effect is expected in the divergent exhaust tailpipe having outlet 726, where the velocity of outflowing jetstream 723 reaches a value u.sub.e higher than the velocity u.sub.* corresponding to the critical condition point 728. In an exemplary embodiment of the present invention, an optimal shape of tunnel 722 provides that the value u.sub.e is lower than the speed of sound u.sub.sound. Outflowing jetstream 723 brings the kinetic power acquired at the expense of the flow warmth. The acquired kinetic power of outflowing jetstream 723 may be high as or even become higher than the power consumed to compensate drag, defined by a drag coefficient corresponding to a concave shape of the inner converging reservoir 721, and thereby to maintain the flying velocity u.sub.a of capsule 720. Capsule 720 is interpreted as a motionless dragging-jet engine.

(325) Outer airfoil side 729 of capsule corpus 720 provides laminar-like flowing of wind outer sub-portions 731 and 732, moving adjacent to outer airfoil side 729 and being subjected to the Coanda-effect operation and, thereby, attracted to the nearby surfaces of outer airfoil side 729. Outflowing jetstream 723 having the decreased static pressure sucks outer sub-portions 731 and 732. The cumulative confluence of sub-portions 731, 732, and 723 constitutes cumulative jetstream 734, associated with the airfoil corpus of capsule 720. In general, the formed cumulative jetstream 734, composed of sub-portions 731, 732, and 723, is turbulent; however, in an optimal case, the turbulence can be suppressed substantially. For simplicity, consider a case of a laminar-like cumulative jetstream 734, “bordered” by streamlines 733. On the one hand, the velocities of outer sub-portions 731 and 732, being lower than the critical condition velocity u.sub.*, are increasing as the attracted outer sub-portions enter the space of cumulative jetstream 734, where the velocities increase is accompanied by a constriction of outer sub-portions 731 and 732, in accordance with equation (6.13). On the other hand, at outlet 726, the velocity of inner sub-portion 723 is of value u.sub.e higher than the critical condition velocity u.sub.*. According to equation (6.13), the velocity of inner sub-portion 723 is decreasing as the sub-portion enters the space of cumulative jetstream 734, where inner sub-portion 723 is constricting as well. If the case is optimized such that the both constrictions are identical, cumulative jetstream 734 is expected to be laminar-like indeed. Bordering streamlines 733 constitute an imaginary convergent-divergent jet-nozzle comprising a narrow throat having the minimal cross-sectional area at the outer critical condition point 738, where the effective M-velocity of cumulative jetstream 734 reaches the specific value M.sub.*=√{square root over ((γ−1)/γ)}. If, upstream-afore the outer critical condition point 738, the effective M-velocity of cumulative jetstream 734 is lower than the specific M-velocity M.sub.*, then the M-velocity of cumulative jetstream 734 is increasing as cumulative jetstream 734 moves such that oufflowing divergent portion 735 has M-velocity higher than M.sub.* downstream-behind the outer critical condition point 738; and vice versa, if, upstream-afore the outer critical condition point 738, the effective M-velocity of cumulative jetstream 734 is higher than the specific M-velocity M.sub.*, then the M-velocity of cumulative jetstream 734 is decreasing as cumulative jetstream 734 moves such that oufflowing divergent portion 735 has the M-velocity lower than the specific M-velocity M.sub.*.

(326) In view of the foregoing description referring to FIG. 7c, it will be evident to a person skilled in the art that: The shape of tunnel 722 can be optimized to provide that the velocity value u.sub.e of oufflowing jetstream 723 becomes higher than the speed of sound u.sub.sound. As well, it will be evident to a person skilled in the art that the shape of tunnel 722 and outer airfoil side 729 of capsule 720 can be optimized to provide that oufflowing divergent portion 735 has increasing M-velocity reaching values higher than the specific M-velocity M.sub.*; Supplying a flying vehicle or helicopter's propeller blades by nozzles similar to capsule 720 operating as jet-booster, one could save fuel consumption substantially and even provide a stable motion against a drag and skin-friction resistance entirely with no fuel burning at all. As well, it will be evident to a person skilled in the art that this is not a so-called “Perpetuum mobile”, but the use of ambient fluid heat to produce useful motion, strictly according to the Energy Conservation Law. Furthermore, looking ahead referring to FIGS. 9d, 9e, and 9f described hereinafter, point out that an even number of such jet-boosters, attached to the even number of blades of a helicopters propeller, result in stabilization of the effective velocities of incoming and outhowing jetstreams associated with the jet-boosters. The predictably equalized velocities enable easier controllable lift-forces when the helicopter is flying speedily; The described airfoil capsule can be stationary exposed to oncoming wind (either natural or artificial) and thereby become applicable to efficient harvesting of electricity providing a positive net-efficiency; and One can further aggregate the open outlet of a specifically shaped convergent-divergent tunnel with an engine using the enhanced jet-effect providing an extra-accelerated and extra-cooled jetstream oufflowing through the open outlet; wherein the engine is either a jet-engine, and/or a turbo-jet engine, and/or a motor applied to a vehicle, and/or a generator of electricity, and/or a cooler, and/or a Peltier element operating as thermoelectric generator, and/or vapor-into-water condenser.

(327) FIG. 7d is a schematic sectional view of a flying capsule 740, constructed according to the principles of the present invention. Flying capsule 740's profile in a sagittal plane has an airfoil outer contour and a contour of a specifically shaped two-stage inner tunnel. In contrast to flying capsule 720 illustrated hereinbefore referring to FIG. 7c, capsule 740 flies with a de Laval high M-velocity, i.e. higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, and the two-stage inner tunnel is shaped similar to the tunnel of two-stage convergent-divergent jet-nozzle 690, described above with reference to FIG. 6h. Namely, the two-stage inner tunnel comprises two narrow throats providing for two associated critical condition points 741 and 742. The oncoming fast flow 743 enters the open inlet 744 of the inner tunnel with a de Laval high M-velocity, higher than the specific M-velocity M.sub.*. Then flow 743 is gradually slowing down, becoming warmer and more compressed as moving to critical condition point 741 where reaching the specific M-velocity M.sub.*, further, is gradually extra-slowing, extra-warming and extra-compressing as moving to reservoir 745, according to equation (6.13), further, is gradually accelerating, cooling, and becoming decompressed as moving to critical condition point 742 where again reaching the specific M-velocity M.sub.*, and further, is gradually extra-accelerating, extra-cooling, and extra-decompressing as moving to outlet 746, as described hereinbefore with references to FIGS. 6a, 6b, 6f, 6g, and 6h.

(328) The cross-section of outlet 746 is wider than the cross-section of inlet 744, thereby providing for that capsule 740 operates as a jet-booster launching a widened and cooled outhowing jetstream 747 with a high M-velocity, higher than the de Laval high M-velocity of oncoming fast flow 743.

(329) Improved Propeller and Ventilator

(330) FIG. 7e is a schematic drawing of improved blowing propeller or ventilator 770, constructed according to the principles of the present invention, to operate in fluid surroundings. For simplicity and without loss of the description generality, consider improved blowing ventilator 770 operating in an open air space. Improved blowing ventilator 770, defined by the main functionality to launch a jetstream characterized by the flow headway-motion kinetic-power, has an inherent engine, which is not shown here, consuming either a power of burned fuel or an electric power and operating in a steady-state mode. Improved blowing ventilator 770 comprises airfoil blades: first-airfoil-blades 772.1 and second-airfoil-blades 772.2, shown here schematically, each, when compounded with imaginary sagittal axis 771, having a chiral asymmetrical shape, wherein, preferably, the shape of first-airfoil-blades 772.1 is substantially mirror-symmetrical relative to the shape of second-airfoil-blades 772.2. First-airfoil-blades 772.1 and second-airfoil-blades 772.2 are forcedly rotating in transitional space “T7”, marked schematically as a cylindrical space portion between frontal planes 779.1 and 779.2. Mutually complemental first-airfoil-blades 772.1 and second-airfoil-blades 772.2 are forcedly rotating in mutually-opposite directions, indicated by curved arrows marked by reference numerals 773.1 and 773.2, correspondingly. Forcedly mutually-opposite rotating first-airfoil-blades 772.1 and second-airfoil-blades 772.2 cover effective cross-section 774, and, thereby, entrap and suck air portions 775.A from space “A1”, which is located upstream-afore effective cross-section 774, and convert flowing air portions 775.A into accelerated jetstream 775.B entering space “B7”, which is located downstream-behind effective cross-section 774. Space “A1”, comprising airflow portions 775.A subjected to the sucking and motion through effective cross-section 774, is bordered by streamlines of airflow 775.A, forming imaginable contours 776.A. The imaginary contours 776.A separate space “A7” from space “C7”, comprising air portions 775.C, drawn by airflow 775.A and flowing toward transitional space “T7” out of effective cross-section 774. Space “B7”, comprising jetstream 775.B, is bordered by streamlines, forming imaginable contours 776.B. The imaginary contours 776.B separate space “B7” from space “D7”, comprising air portions 775.D, drawn by jetstream 775.B and flowing downstream-behind transitional space “T7”. In contrast to the general case, when a complicated motion of air portions 775.A, 775.B, 775.C, and 775.D comprises both: a headway-motion, i.e. a laminar component of motion aligned with the imaginary contours 776.A and 776.B having a prevalent direction along imaginary sagittal axis 771, and a whirling-motion, i.e. a turbulent component of motion, dominantly, whirling around imaginary sagittal axis 771; the forcedly mutually-opposite rotating first-airfoil-blades 772.1 and second-airfoil-blades 772.2 are optimized to prevent the power-consuming whirling motion and provide the desired dominant headway-motion of air portions 775.A, 775.B, 775.C, and 775.D, as one of the primary features of improved blowing ventilator 770. For simplicity, further describing the optimized case, minor effects caused by the whirling turbulence will be ignored. In the optimized case, the power, consumed by the inherent engine of improved blowing ventilator 770, dominantly, is expended for: the headway-motion of air portions 775.A, which then are transformed into jetstream 775.B; the directional motion of air portions 775.C, which then are transformed into moving air portions 775.D; the overcoming of air viscous-resistance; and the compensation of inner resistance of the inherent engine.
Wherein the part of the power consumption, expended on the overcoming of air viscous-resistance and compensation of inner resistance of the inherent engine, dissipates in the acquired warmth of oufflowing air portions 775.B and 775.D.
Mutually-opposite rotating first-airfoil-blades 772.1 and second-airfoil-blades 772.2 have optimized shapes, in addition providing a certain focusing of jetstream 775.B, such that streamlines 776.A and 776.B constitute an imaginary convergent-divergent tunnel. Furthermore, the speeds of first-airfoil-blades 772.1 and second-airfoil-blades 772.2 mutually-opposite rotations are optimized such that jetstream 775.B moves through cross-section 778.B of the minimal area with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, thereby making the imaginary convergent-divergent tunnel, constituted by streamlines 776.A and 776.B, in principle, similar to the specifically shaped tunnel of convergent-divergent jet-nozzle 610 shown in FIG. 6a, wherein imaginary sagittal axis 771 and imaginary sagittal x-axis 615 (FIG. 6a) are collinear, effective cross-section 774 takes the place of imaginary inlet 6131 (FIG. 6a), and cross-section 778.B of the minimal area provides the critical condition for the de Laval effect triggering. Thus, the imaginary convergent-divergent tunnel, constituted by streamlines 776.A and 776.B, performs a de Laval-like nozzle. A de Laval-like jet-effect, which is similar to the classical de Laval jet-effect but arising in the de Laval-like nozzle having imaginary walls formed by streamlines 776.A and 776.B of the flowing air, is triggered, as described hereinbefore referring to FIGS. 6a, 6b, 6c, 6d, and 6e, thereby resulting in an extra-acceleration and extra-cooling of jetstream 775.B immediately downstream-behind cross-section 778.B. This provides one of the primary features of improved blowing ventilator 770.

(331) The de Laval-like nozzle, having imaginary convergent-divergent tunnel formed by streamlines 776.A and 776.B of the flowing air, geometrically, is not identical with an optimized de Laval nozzle having solid walls, described hereinbefore referring to FIGS. 6a, 6b, 6c, 6d, and 6e, at least because of the osmotic-like effect inherently occurring on imaginary contours 776.A and 776.B, as described above with references to FIGS. 4 and 5b. The osmotic-like effect is defined as an effect of exchange of molecular matter and heat between moving air portions. The osmotic-like effect includes a mutually-directed effect of diffusion, occurring because of both: the Brownian random motion of the fluid's molecules, and the effect of molecules motion in a cross-sectional plane, caused by the gradients of fluid density Δρ and temperature ΔT in the cross-sectional plane, which are interrelated with the jetstream 775.B convergent-divergent motion. The osmotic-like effect, reducing the gradients, is accumulative, making equation (6.13) applicable qualitatively to a local neighborhood of a coordinate at sagittal axis 771 only.

(332) Since a certain distance downstream-behind cross-section 778.B of minimal area, namely, in transitional space “E7”, marked schematically as a cylindrical space portion between frontal planes 779.3 and 779.4, the extra-accelerated jetstream 775.B, subjected to a diffusion of molecules of air portions 775.D as the airflow moving along sagittal axis 771, becomes transformed into transitional jetstream 775.E, characterized by a local maximum of cross-sectional area, where the density and temperature of transitional jetstream 775.E are already not reducing and a high M-velocity of transitional jetstream 775.E, being higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, is not increasing more.

(333) Farther, in space “F7” located downstream-behind transitional space “E7”, transitional jetstream 775.E is transformed into slowing jetstream 775.F, which, according to equation (6.13) qualitatively applicable to a local neighborhood, is characterized by an increase of airflow density and temperature. Slowing jetstream 775.F, bordered by convergent-divergent streamlines 776.F, reaches cross-section 778.F of minimal area, where the M-velocity of jetstream 775.F reverts to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} and the de Laval-like retarding-effect is triggered resulting in an extra-slowing and extra-warming of jetstream 775.F downstream behind cross-section 778.F of minimal area, as described hereinabove referring to FIGS. 6f and 6g, relating to jet-nozzle 650, having solid walls.

(334) Gradual variations of the air thermodynamic parameters are expected in the open space, thereby providing optimized shapes of imaginary contours 776.A, 776.B, 776.E, and 776.F. These optimizations result in that improved blowing ventilator 770: on the one hand, powered by the inherent engine, expends the power for: the headway-motion of air portions 775.A, further transformed into directional jetstreams 775.B, 775.E, and 775.F, the directional motion 775.C, further transformed into directional motion 775.D, the overcoming of air viscous-resistance, and the compensation of inner resistance of the inherent engine; and on the other hand, triggering the de Laval-like jet-effect in an adiabatic process, saves the power for the jetstream 775.B acceleration and extra-acceleration, correspondingly, upstream-afore and downstream-behind cross-section 778.B, providing one of the primary features of improved blowing ventilator 770.

(335) The resulting functionality net-efficiency of improved blowing ventilator 770 is defined by the ratio of the kinetic-power of launched jetstream 775.E to the power, consumed by the inherent engine of improved blowing ventilator 770.

(336) In view of the foregoing description referring to FIG. 7e, it will be evident to a person skilled in the art that improved blowing ventilator 770 provides for jetstream 775.B launching and further acceleration and extra-acceleration at the expense of both: the power of inherent engine and the warmth of ambient air, so the resulting functionality net-efficiency of improved blowing ventilator 770 may exceed 100%. Furthermore, improved blowing propeller 770, having the resulting functionality net-efficiency higher than 100% and pushing a vehicle, in the final analysis, can operate at the expense of ambient warmth only.

(337) In view of the foregoing description referring to FIG. 7e, it will be evident to a person skilled in the art that, to implement an improved blowing ventilator, having real corpus 777 occupying a certain space, comprising a part of transitional space “T7”, one should implement real corpus 777 as a fragment of a convergent-divergent tunnel for air portions 775.A and jetstream 775.B, applying principles of the present invention to an optimization of the tunnel shape, in order to suppress undesired power-consuming shock and Mach waves, as described hereinabove referring to FIGS. 6a, 6b, 6c, 6d, and 6e. As well, it will be evident to a person skilled in the art that real corpus 777 of an improved blowing ventilator may have real walls, occupying also substantial portions of spaces “A7” and “B7”, implementing optimized contours 776.A and 776.B now becoming actual, such that the improved blowing ventilator comprises a real specifically shaped convergent-divergent tunnel having a narrow throat with the critical condition point, as described hereinabove referring to FIG. 6a. As well, it will be evident to a person skilled in the art that an improved blowing ventilator can be used to accelerate and focus an ionized gas, i.e. plasma, controlled by an external magnetic field, wherein the geometry of the imaginary walls, formed by streamlines 776.A and 776.B, can be controlled by the magnetic field, such that the imaginary walls, occupying substantial portions of spaces “A7” and “B7”, form a specifically shaped convergent-divergent tunnel having narrow throat with the critical condition point, as described hereinabove referring to FIG. 6a.

(338) In view of the foregoing description referring to FIG. 7e, it will be evident to a person skilled in the art that one can implement transitional space “T7” of an improved propeller, characterized by the primary features of improved blowing ventilator 770, using a pair of rotating airfoil Archimedes screws having helically coiled airfoil-profiled walls, similar to walls of spirals 592 and 593, described hereinbefore referring to FIG. 5i, instead of the use of rotating first-airfoil-blades 772.1 and second-airfoil-blades 772.2. As well, transitional space “T7” can be implemented using a combination of many rotating airfoil blades and stationary or rotating airfoil screws of Archimedes.

(339) FIG. 7f is a schematic drawing of improved sucking propeller or ventilator 780, constructed according to the principles of the present invention to operate in fluid surroundings. For simplicity and without loss of the description generality, consider improved sucking ventilator 780 operating in an open air space. Improved sucking ventilator 780 is defined by the main functionality, being inverse to the main functionality of improved blowing ventilator 770, described above with the reference to FIG. 7e, namely, to make an incoming jetstream, characterized by the flow headway-motion kinetic-power. Looking ahead, point out that improved sucking ventilator 780, constructed according to the principles of the present invention, is as inverse improved blowing ventilator 770. Improved sucking ventilator 780 has an inherent engine, which is not shown here, consuming either a power of burned fuel or an electric power and operating in a steady-state mode. Improved sucking ventilator 780 comprises airfoil blades: first-airfoil-blades 782.1 and second-airfoil-blades 782.2, which are shown schematically, each having an asymmetrical and chiral geometrical configuration, wherein, preferably, the geometrical configuration of first-airfoil-blades 782.1 is mirror-symmetrical relative to the geometrical configuration of second-airfoil-blades 782.2. Mutually complemental first-airfoil-blades 782.1 and second-airfoil-blades 782.2 are forcedly rotating in transitional space “T8”, marked schematically as a cylindrical space portion between frontal planes 789.1 and 789.2. First-airfoil-blades 782.1 and second-airfoil-blades 782.2 are forcedly rotating in mutually-opposite directions, indicated by curved arrows marked by reference numerals 783.1 and 783.2, correspondingly. First-airfoil-blades 782.1 and second-airfoil-blades 782.2 have geometrical configurations such that, when forcedly mutually-opposite rotating and covering effective cross-section 784, entrap and suck incoming jetstream 785.B from space “B8”, which is located upstream-afore effective cross-section 784, convert incoming jetstream 785.B into defocusing airflow 785.A, divergently entering space “A8”, which is located downstream-behind effective cross-section 784.

(340) Incoming jetstream 785.B, subjected to the sucking, is bordered by streamlines forming imaginary contours 786.B. The imaginary contours 786.B separate space “B8” from space “D8”, comprising air portions 785.D, drawn by incoming jetstream 785.B and flowing toward transitional space “T8” out of effective cross-section 784. Space “A8”, comprising divergent airflow 785.A, is bordered by streamlines forming imaginary contours 786.A. The imaginary contours 786.A separate space “A8” from space “C8”, comprising air portions 785.C, drawn by divergent airflow 785.A and flowing downstream-behind transitional space “T8”. Forcedly mutually-opposite rotating first-airfoil-blades 782.1 and second-airfoil-blades 782.2 are optimized to prevent the power-consuming whirling motion and provide the desired dominant headway-motion of air portions 785.A, 785.B, 785.C, and 785.D, as one of the primary features of improved sucking ventilator 780.

(341) Mutually-opposite rotating first-airfoil-blades 782.1 and second-airfoil-blades 782.2 have optimized shapes, in addition providing a certain defocusing of incoming jetstream 775.B, such that streamlines 786.B and 776.A constitute an imaginary convergent-divergent tunnel. Furthermore, the mutually-opposite rotations speeds are optimized such that incoming jetstream 785.B moves through cross-section 788.B of the minimal area with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, thereby making the imaginary convergent-divergent tunnel, constituted by streamlines 786.B and 786.A, similar to the specifically shaped tunnel of convergent-divergent jet-nozzle 650 shown in FIG. 6f, wherein imaginary sagittal axis 781 and imaginary sagittal x-axis 655 (FIG. 6f) are collinear, effective cross-section 784 takes the place of imaginary outlet 6532 (FIG. 6f), and cross-section 788.B of the minimal area provides the critical condition for the de Laval effect triggering. Thus, the imaginary convergent-divergent tunnel, constituted by streamlines 786.B and 786.A, performs an inverse de Laval-like nozzle. A de Laval-like retarding-effect, which is similar to the classical de Laval retarding-effect described hereinbefore referring to FIG. 6f but occurring in the inverse de Laval-like nozzle having imaginary walls formed by streamlines 786.B and 786.A of the flowing air, is triggered, thereby resulting in an extra-slowing and extra-warming of incoming jetstream 785.B immediately downstream-behind cross-section 788.B. Furthermore, the condition of incoming jetstream 785.B moving through cross-section 788.B of the minimal area with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} interrelates with the condition of extra-pre-acceleration of incoming jetstream 785.B just upstream-afore cross-section 788.B, according to equation (6.13) qualitatively applicable to a local neighborhood. Thus, the M-velocity of incoming jetstream 785.B just upstream-afore cross-section 788.B is higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. This provides one of the primary features of improved sucking ventilator 780.

(342) Furthermore, again, according to equation (6.13) qualitatively applicable to a local neighborhood, the high M-velocity, higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, can be reached due to the direct de Laval-like jet-effect in an earlier pre-history of incoming jetstream 785.B, namely, in space “F8” comprising pre-incoming jetstream 785.F moving through imaginary convergent-divergent tunnel constituted by streamlines 786.F and having cross-section 788.F of a local minimum area providing the critical condition. Then the accumulative osmotic-like effect results in that since a certain distance downstream-behind cross-section 788.F of local minimum area, namely, in transitional space “E8”, marked schematically as a cylindrical space portion between frontal planes 789.3 and 789.4, pre-incoming jetstream 785.F, subjected to a diffusion of air molecules as moving along sagittal axis 781, becomes transformed into transitional jetstream 785.E, characterized by a local maximum of cross-sectional area, where the density and temperature of transitional jetstream 785.E are already not reducing and the M-velocity of transitional jetstream 785.E, being higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, is not increasing more. Transitional jetstream 785.E becomes transformed into incoming jetstream 785.B subjected to the de Laval-like retarding-effect resulting in incoming jetstream 785.B slowing and extra-slowing. Thus, relatively slow divergent airflow 785.A has an upstream pre-history, comprising the pre-accelerated and extra-pre-accelerated headway-motion of jetstream 785.B downstream-behind and upstream-afore cross-section 788.B, correspondingly, wherein gradual variations of the air thermodynamic parameters are expected in the open space, thereby providing optimized shapes of imaginary contours 786.B and 786.A. These optimizations result in that improved sucking ventilator 780: on the one hand, powered by the inherent engine, expends the power for: the headway-motion of pre-incoming jetstream 785.F, further transformed sequentially into directional motion of transitional jetstream 785.E, incoming jetstream 785.B, and divergent airflow 785.A, the directional motion of outer portions 785.D, further transformed into directional motion of outer portions 785.C, the overcoming of air viscous-resistance, and the compensation of inner resistance of the inherent engine; and on the other hand, triggering the de Laval-like retarding-effect having pre-history comprising the de Laval-like jet-effect in an adiabatic process, saves the power for the incoming jetstream 785.B motion, accelerated and pre-extra-accelerated, correspondingly, downstream-behind and upstream-afore cross-section 788, providing one of the primary features of improved sucking ventilator 780.

(343) The resulting functionality net-efficiency of improved sucking ventilator 780 is defined by the ratio of the kinetic-power of sucked transitional jetstream 785.E to the power, consumed by the inherent engine of improved sucking ventilator 780.

(344) In view of the foregoing description referring to FIG. 7f, it will be evident to a person skilled in the art that improved sucking ventilator 780 provides for pre-incoming jetstream 785.F sucking pre-acceleration and extra-pre-acceleration at the expense of both: the power of inherent engine and the warmth of ambient air, so the resulting functionality net-efficiency of improved sucking ventilator 780 may exceed 100%. Furthermore, improved sucking propeller 780, having the resulting functionality net-efficiency higher than 100% and pulling a vehicle, in the final analysis, can operate at the expense of ambient warmth only.

(345) It will be further evident to a person skilled in the art that, to implement an improved sucking ventilator, having real corpus 787 occupying a certain space, comprising a part of transitional space “T8”, one should implement real corpus 787 as a fragment of a convergent-divergent tunnel for incoming jetstream 785.B and divergent airflow 785.A, applying principles of the present invention to an optimization of the tunnel shape, in order to suppress undesired power-consuming shock and Mach waves, as described hereinabove referring to FIGS. 6a, 6b, 6c, 6d, 6e, and 6f. As well, it will be evident to a person skilled in the art that real corpus 787 of an improved sucking ventilator may have real walls, occupying also substantial portions of spaces “B8” and “A8”, implementing optimized contours 786.B and 786.A now becoming actual, such that the improved sucking ventilator comprises a real specifically shaped convergent-divergent tunnel having a narrow throat with the critical condition point, as described hereinabove referring to FIG. 6f.

(346) In view of the foregoing description referring to FIGS. 7e and 7f, it will be evident to a person skilled in the art that one can: implement the schematically shown mutually-opposite rotating and mutually complemental airfoil blades using many relatively small mutually-opposite rotating and mutually complemental airfoil blades, distributed spatially, altogether providing the mentioned primary features of an improved blowing and/or sucking propeller and/or ventilator; cascade an improved sucking propeller and an improved blowing propeller such that imaginary sagittal axis 771 is as a continuation of imaginary sagittal axis 781, and space “A7” follows downstream behind space “A8”, thereby creating a combined improved sucking-and-blowing propeller. A vehicle, supplied with such a combined improved sucking-and-blowing propeller, provides for an optimized motion with a reduced drag; and implement transitional space “T7” and/or “T8” of an improved propeller, characterized by the primary features of improved blowing ventilator 770 and/or improved sucking ventilator 780, correspondingly, as a not obligatorily connected transitional space, but comprising several separate sub-spaces, each defined by at least one smaller propeller.

(347) In view of the foregoing description referring to FIGS. 7e and 7f, in combination with the foregoing description referring to FIGS. 5h, 5j, and 5k, it will be evident to a person skilled in the art that one can implement a device, similar to improved blowing and/or sucking propeller 770 and/or 780, correspondingly, but comprising first-airfoil-blades 772.1 and/or 782.1 and second-airfoil-blades 772.2 and/or 782.2, both remain stationary, wherein the device, having no moving parts, is submerged in water surroundings, and wherein at least some sides of the stationary airfoil blades are covered with a hydrophobic material, that provides creating of a launched and/or sucked water jetstream at the expense of the water warmth only. Furthermore, estimations, made referring to FIG. 5h, show that a big quantity of such small hydrophobic-propellers, in particular, comprising stationary but hydrophobic blades, altogether cumulatively functioning like an improved launching and/or sucking propeller, can provide a powerful water jetstream that can be used, in particular, for pushing a submarine at the expense of the water warmth.

(348) Wing as a Convergent-Divergent Jet-Nozzle

(349) FIG. 8a is a schematic visualization 800 of an oncoming wind portion 820, without loss of generality, moving horizontally. Oncoming wind portion 820 comprises airflow sub-portions 821, 822, 823, and 824 flowing around actually-airfoil wing 810, having a sectional profile, constructed according to the principles of the present invention. The upper side of actually-airfoil wing 810 comprises: (a) a forward part meeting upper sub-portion 822 having imaginary cross-section 831; (b) a withers defined as the highest point on the upper side of the airfoil profile convexity, where sliding sub-portion 822 has imaginary narrowed cross-section 832, and (c) a rearward part, attracting and, thereby, redirecting the mass-center of the upper sliding sub-portion 822 backward-downward, where sliding sub-portion 822 has imaginary widened cross-section 833.

(350) When airflow sub-portions 821, 822, 823, and 824 are flowing around actually-airfoil wing 810, the streamlines [not shown here] of sub-portions 822 and 823, flowing near actually-airfoil wing 810, are curving in alignment with the airfoil-profile, the streamlines [not shown here] of portions 821 and 824, flowing farther from actually-airfoil wing 810, keep substantially straight trajectories aligned with imaginary horizontal lines 811 and 812 correspondingly above and under actually-airfoil wing 810.

(351) Actually-airfoil wing 810's surface material properties, porosity, and structure are elaborated according to the principles of the present invention such that air sub-portions 822 and 823 are subjected to the Coanda-effect, defined by the partial pressure-c δP.sub.c, rather than to the skin-friction resistance, occurring in an imaginary boundary layer and being quantified by the difference (a.sub.w−a−δa). Imaginary lines 811 and 812 can be considered as imaginary walls, thereby, together with the airfoil-profile forming imaginary nozzles. The upper imaginary nozzle comprises imaginary cross-sections 831, 832, and 833, and the lower imaginary nozzle comprises imaginary cross-sections 834 and 835. Cross-section 831 is wider than cross-section 832 and cross-section 832 is narrower than cross-section 833, thereby, the upper imaginary nozzle has a convergent-divergent shape and sliding sub-portion 822 represents a convergent-divergent jetstream while flowing through cross-sections 831, 832, and 833. Cross-section 834 is wider than cross-section 835, so the lower imaginary nozzle has a converging shape. Consider a case, when actually-airfoil wing 810 flies with a de Laval low M-velocity M.sub.810 that is lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach≈664 km/h, but such that sliding sub-portion 822, moving through the upper imaginary nozzle, reaches the specific M-velocity M.sub.* when passes through the narrowest cross-section 832. So, the de Laval-like jet-effect arising is expected above actually-airfoil wing 810, i.e. within the upper imaginary convergent-divergent jet-nozzle. This is accompanied by the static pressure decrease and extra-decrease, as described hereinabove with the reference to FIG. 6b, and thereby results in the lift-effect, becoming stronger. In frames of the aerodynamics, one estimates the narrowest cross-section 832 linear size, i.e. thickness of a so-called “boundary layer”, normalized to a so-called “characteristic size” of the considered wing, as proportional to so-called Reynolds Number. As well, the thickness of boundary layer can be specified experimentally for a kind of body corpuses. In view of the foregoing description referring to FIG. 6a and FIG. 8a, it will be evident to a person skilled in the art that, basing on the defined narrowest cross-section 832 linear size as the thickness of boundary layer, one can apply the equation of M-velocity (6.13) to design an improved profile of the wing.

(352) In view of the foregoing description referring to FIG. 8a, it will be evident to a person skilled in the art that the described de Laval-like jet-effect is similar to the classical de Laval jet-effect, but arising in an optimized convergent-divergent tunnel having imaginary walls formed by streamlines of a flow.

(353) Namely, the specifically shaped convergent-divergent tunnel comprises two opposite walls; wherein one of the two opposite walls is constructed from a solid material and another of the two opposite walls is imaginary and formed by streamlines of the flowing fluid subjected to the Coanda-effect operation.

(354) Thus, a method for a wing profile design, based on equation (6.13) according to an exemplary embodiment of the present invention, allows optimizing the wing airfoil shape to reach the best efficiency of the lift-effect as a result of the enhanced jet-effect occurring above the wing. The inventor notes that the profile of the actually-airfoil wing 810 designed and optimized using the equation (6.13) has a shape similar to a shape of a birdwing rather than to the shape of the classic wing of airplane.

(355) The Coanda-Effect Operation Providing an Imaginary Convergent-Divergent Nozzle

(356) FIG. 8b is a schematic illustration of a flying airfoil body 840 having the shape of an elongated drop. For simplicity and without loss of reasoning, the shape is axis-symmetrical around the longitudinal axis 841. The airfoil body 840 comprises: a forward part meeting oncoming flow portion 851; a “withers”, defined as the highest point on the upper side of the airfoil profile, where sliding sub-portion 853 has an imaginary narrowed cross-section 868, and a rearward part.

(357) When an oncoming air portion 851, originally having a cross-sectional area 861, is running at the forward part of flying body 840, it is subjected to the Coanda-effect operation resulting in air portion 851 reshaping, and thereby forming an ambient-adjoining convergent-divergent jetstream, comprising sliding sub-portions: 852 being convergent, 853 being narrow and having imaginary narrowed cross-section 868 of the minimal cross-sectional area, 854 being divergent, and 855 becoming convergent due to the Coanda-effect attraction. Body 840's surface material properties, porosity, and structure are implemented according to the principles of the present invention, thereby providing that air portion 851 is subjected to the Coanda-effect, defined by the partial pressure-c δP.sub.c, rather than to the skin-friction resistance, occurring in an imaginary boundary layer and being quantified by the difference (a.sub.w−a−δa). Furthermore, sliding sub-portions 855, join together, forming the resulting cumulative air portion 856. Oncoming air portion 851 and all the mentioned derivative sub-potions move within space “bordered” by imaginary walls marked by dashed contours 842. The imaginary walls 842 together with the airfoil surface of body 840 constitute an imaginary tunnel. The tunnel's cross-section gradually constricts from the inlet cross-section 862 to the narrowest cross-section 868 and then gradually widens up to the outlet cross-section 863. I.e. sliding sub-portions 852 are shrinking while reaching the withers of airfoil body 840, where the cross-sections 868 of sub-portions 853 become minimal. Then, behind the withers, the cross-sections of sub-portions 854 and 855 are widening as moving.

(358) Sliding sub-portions 855, being under the subjection of the Coanda-effect operation, turn aside in alignment with the slippery surfaces of airfoil body 840's rearward part and join together, forming the resulting air portion 856. It results in a convergence of resulting air portion 856, i.e. in that, cross-section 864, located farther downstream, becomes narrower than cross-section 863 located immediately behind airfoil body 840, and opposite streamline-fragments 843 form an imaginary convergent funnel. Furthermore, opposite streamline-fragments 844, which are bordering flow portion 857, constitute an imaginary divergent stage of a tunnel downstream-behind the narrowest cross-section 864. The converging opposite streamline-fragments 843 and divergent opposite streamline-fragments 844 together constitute the imaginary convergent-divergent tunnel, and, correspondingly, portions 856 and 857 together constitute an outilowing convergent-divergent jetstream.

(359) Jet-Booster Based on the Venturi Effect

(360) First, consider a case, when airfoil body 840 flies with a Venturi M-velocity, i.e. with a low M-velocity, lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach, and low sufficient to provide that M-velocity M.sub.868 of accelerated sliding sub-portions 853, passing cross-sections 868 over the withers, and M-velocity M.sub.864 of accelerated sub-portions 856, passing through the narrowest cross-section 864, both remain lower than the specific M-velocity M.sub.*, i.e. M.sub.868<M.sub.* and M.sub.864<M.sub.*. In this case, the narrowest cross-section 864 of outflowing air portion 856 is narrower than the original cross-section 861 of oncoming air portion 851, and the M-velocities M.sub.861, M.sub.863 M.sub.864 M.sub.865 and M.sub.868, where the indices correspond to markers of associated cross-sections, satisfy the following conditions:
M.sub.861<M.sub.868<M.sub.*,
M.sub.863<M.sub.868<M.sub.*,
M.sub.863<M.sub.864<M.sub.*,
M.sub.861<M.sub.864<M.sub.*, and
M.sub.865<M.sub.864<M.sub.*.
Thus, body 840 operates as a jet-booster basing on the Venturi effect occurring in the imaginary tunnel adjacent to body 840's surfaces.

(361) A practical application of the phenomenon that, under certain conditions, outflowing portion 856, moving through the narrowest cross-section 864, has a velocity higher than the velocity of oncoming portion 851 is one of the primary teachings of the present invention.

(362) Jet-Boosters Based on the De Laval-Like Jet-Effect

(363) Secondly, consider a case, when airfoil body 840 flies relatively slowly, such that sliding sub-portions 853 pass cross-sectional areas 868 with an M-velocity that remains lower than the specific M-velocity, i.e. M.sub.853<M.sub.*, but high sufficient to provide that the increased M-velocity of portion 856 is higher than M-velocity of sub-portions 853 and reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the critical condition point 864. In this case, M-velocity M.sub.863 is the de Laval low velocity and the de Laval-like jet-effect is triggered, resulting in that the M-velocity of the divergent flow portion 857 exceeds the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. In this case, the M-velocities M.sub.861, M.sub.863, M.sub.864 M.sub.865, and M.sub.868 satisfy the following conditions:
M.sub.861<M.sub.868<M.sub.*,
M.sub.863<M.sub.868<M.sub.*,
M.sub.863<M.sub.864=M.sub.*,
M.sub.861<M.sub.864=M.sub.*, and
M.sub.865>M.sub.864=M.sub.*,
So, body 840 operates as a jet-booster basing on the de Laval-like jet-effect occurring in the imaginary tunnel downstream-behind airfoil body 840.

(364) Thereby, the Coanda-jet-effect operation forcedly forms convergent-divergent laminar-like streamlines downstream-behind airfoil body 840, wherein the static pressure is distributed gradually along the convergent-divergent laminar-like streamlines that provides an optimized extension of air portion 857 resulting in the de Laval-like enhanced jet-effect accompanied by extra-cooling and extra-acceleration of air portion 857. This is one more teaching of the present invention.

(365) A practical application of the phenomenon that, under certain conditions, outhowing portion 857 has an M-velocity higher than the specific M-velocity is one of the primary teachings of the present invention.

(366) It will be evident to a person skilled in the art that the enhanced jet-effect results in an optimized reactive thrust-force applied to airfoil body 840.

(367) Thirdly, consider a case, when airfoil body 840's shape is optimized using the equation of M-velocity (6.13), basing on an estimated linear size of cross-section 868, and when airfoil body 840 flies with a de Laval low M-velocity M.sub.851, i.e. lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach, but high sufficient to provide that M-velocity of sliding sub-portions 853 reaches the value of the specific M-velocity, i.e. M.sub.868=M.sub.* at the critical condition point 868. Thereby, the enhanced de Laval-like jet-effect occurs downstream-behind the withers, providing that M.sub.*<M.sub.854<M.sub.855, where the indexes correspond to associated sliding air sub-portions. In this case, according to equation (6.13), shrinking portion 856, moving with a de Laval high M-velocity, is slowing down, becoming warmer and more compressed, as moving on the way to the critical condition point associated with cross-section 864. The de Laval-like retarding-effect occurs downstream-behind cross-section 864 resulting in portion 857 expanding and further slowing down, warming, and compressing while reaching cross-section 865. The M-velocities M.sub.861, M.sub.863, M.sub.864, M.sub.865, and M.sub.868 satisfy the following conditions:
M.sub.861<M.sub.868=M.sub.*,
M.sub.863>M.sub.868=M.sub.*,
M.sub.863>M.sub.864=M.sub.*,
M.sub.861<M.sub.864=M.sub.*, and
M.sub.865<M.sub.864=M.sub.*.
So, in the final analysis, body 840 operates as a jet-booster, triggering both the de Laval-like jet-effect and the de Laval-like retarding-effect.

(368) Fourthly, consider a case, when airfoil body 840's shape is optimized using the equation of M-velocity (6.13), basing on an estimated linear size of cross-section 868, and when airfoil body 840 flies with a de Laval high M-velocity, i.e. higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach. According to equation (6.13), the de Laval-like retarding-effect occurs in the imaginary convergent-divergent tunnel formed by streamlines 842. Namely, shrinking air potions 852 are slowing down, becoming warmer and more compressed, as moving on the way to withers such that the M-velocity of the narrowest sliding sub-portions 853 reaches the specific M-velocity, i.e. M.sub.868=M.sub.* at the critical condition point 868; and further, portions 854 continue to slow down while expanding downstream-behind the withers. Relatively slowly moving sliding sub-portions 855, now having a de Laval low M-velocity, join downstream-behind cross-section 863, thereby, providing for resulting shrinking portion 856 acceleration, accompanied by a decrease of temperature and static pressure, while reaching again the specific M-velocity M.sub.* at the narrowest cross-section 864. The de Laval-like jet-effect occurs downstream-behind cross-section 864 resulting in expanding portion 857 further acceleration accompanied by a deeper decrease of temperature and static pressure on the way to cross-section 865. So, the M-velocities M.sub.861, M.sub.863, M.sub.864, M.sub.865, and M.sub.868 satisfy the following conditions:
M.sub.861>M.sub.868=M.sub.*,
M.sub.863<M.sub.868=M.sub.*,
M.sub.863<M.sub.864=M.sub.*,
M.sub.861>M.sub.864=M.sub.*, and
M.sub.865>M.sub.864=M.sub.*.
Again, in the final analysis, body 840 operates as a jet-booster, triggering both the de Laval-like retarding-effect and the de Laval-like jet-effect.

(369) In view of the foregoing description referring to FIGS. 6a, 7a, 7b, 7c, 8a and 8b, it will be evident to a person skilled in the art that: a method for an airfoil body shape design, based on equation (6.13) according to an exemplary embodiment of the present invention, allows, modifying the overall geometry of the body, to optimize the efficiency of the enhanced jet-effect occurring outside of the body; the described convergent-divergent jet-nozzles can be applicable to many apparatuses using mechanical and heat energy provided by either a flowing gas or liquid; triggering and controlling the desired de Laval-like jet-effect can be provided by manipulating by the oncoming wind de Laval M-velocity. As the M-velocity is temperature-dependent, one can heat or cool air portions flowing within a specifically shaped tunnel, in particular, in an imaginary tunnel around a flying body; reaching and controlling the desired de Laval-like jet-effect can be provided by manipulating by the value of specific M-velocity, depending on the generalized adiabatic compressibility parameter γ. For example, one can inject a gas composed of multi-atomic particles into a tunnel, in particular, into an imaginary tunnel around a flying body. As well, it will be evident to a person skilled in the art that, for example, micro-flakes-of-snow could play a role of such multi-atomic particles. Another technique to change the generalized adiabatic compressibility parameter γ and thereby to control the specific M-velocity is to ionize the flow, moving through the tunnel; and the described convergent-divergent jet-nozzles can be applicable to many apparatuses using mechanical and heat energy, provided by flowing gas or liquid.

(370) Two-Stage Operation of the Coanda-Jet-Effect

(371) FIG. 8c is a schematic illustration of flying airfoil bodies 850 and 860, arranged such that the withers of airfoil bodies 860 follow downstream-behind the withers of body 850. For simplicity and without loss of reasoning, each airfoil body 850 and 860 has the shape of an elongated drop 840 described above with reference to FIG. 8b. All reference numerals 841, 861, 851, 862, 852, 868, 853, 842, and 854 are the same as described referring to FIG. 8b.

(372) Consider a case, when flying airfoil bodies 850 and 860 meet oncoming portion 851 with a de Laval high M-velocity M.sub.851, higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach. According to equation (6.13), air sub-potions 852 are slowing down as constricting on the way to the withers of body 850, such that M-velocity of the narrowest sliding sub-portions 853 reach the specific M-velocity, i.e. M.sub.853=M.sub.* at the critical condition point 868. The de Laval-like retarding-effect occurs downstream-behind the withers. It provides the condition M.sub.*>M.sub.854, where index “854” corresponds to air sub-portions 854. So, airfoil bodies 860 meet oncoming sub-portions 854 flowing slower than with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, but high sufficient to provide the critical condition near their [bodies 860's] withers. Again, according to equation (6.13), air sub-potions 859 have an M-velocity M.sub.859 higher than the specific M-velocity M.sub.*. Thus, flying airfoil bodies 850 and 860 meet the upstream air portions, and leave the downstream air portions, flowing faster than with the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. Furthermore, a cumulative cross-section of air sub-potions 859, wider than cross-section 861 of oncoming portion 851, means that the M-velocity M.sub.859 is higher than the high M-velocity M.sub.851 of oncoming portion 851. In this case, the Coanda-jet-effect two-stage operation accelerates a portion of ambient airflow that originally moves faster than with the specific M-velocity M.sub.*. Thus, in contrast to the case when a body, having not-optimized shape, flies in air-environment with transonic, and/or supersonic, and/or hypersonic velocities, flying airfoil body 850, operating in tandem with each flying airfoil body 860, moving downstream behind the withers of airfoil body 850, results in a specific effect of acceleration and cooling air portion 851, oncoming faster than with the specific M-velocity M.sub.*. This is one other primary teaching of the present invention.

(373) FIG. 8d is a schematic drawing of a flying wing 870 having a two-humped airfoil profile 871, constructed according to the principles of the present invention. The flying wing 870 comprises two withers: forward 872 and rear 873, separated by concavity 874. The flying M-velocity is higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} ≈0.5345 Mach.

(374) An oncoming flow portion 875 runs at wing 870 and passes positions: 801, 802, 803, 804, 805, 806, 807, 808, and 809 sequentially with associated M-velocities: M.sub.801, M.sub.802, M.sub.803, M.sub.804, M.sub.805 M.sub.806, M.sub.807, M.sub.808, and M.sub.809, correspondingly. The two-humped airfoil profile 871 provides for the Coanda-jet-effect two-stage operation: upstream-afore and downstream-after concavity 874. At position 801, flow portion 875, having the de Laval high M-velocity M.sub.801, is yet to be subjected to the Coanda-jet-effect operation over wing 870's profiled surfaces. The two-humped airfoil profile 871 causes that the cross-sectional area of portion 875 is varying as portion 875 moves over wing 870. So, portion 875 shrinks at position 802 while upping over the forward part, has the first local minimum of cross-section area at position 803 above the forward withers 872, expands at position 804 while downing into concavity 874, reaches the local maximum of cross-section area at position 805 when passing concavity 874, shrinks again at position 806 on the way to the rear withers 873, gets the second local minimal value of cross-section area at position 807 above the rear withers, and expands at positions 808 and 809. According to equation (6.13), portion 875 is subjected to the de Laval-like jet-effect and the de Laval-like retarding-effect such that: at position 802, the flow convergence is accompanied by the de Laval-like retarding-effect resulting in compressing and warming of flow portion 875 and a decrease of M-velocity, i.e. M.sub.801>M.sub.802 at position 803, the first critical condition point, where the varying value of flow portion 875's cross-sectional area has the first local minimum, provides for that the M-velocity of flow portion 875 reaches the specific M-velocity M.sub.*, so, M.sub.801>M.sub.802>M.sub.803=M.sub.*, i.e. the critical condition of the de Laval-like retarding-effect triggering is satisfied; at position 804, the flow divergence is accompanied by further compressing and warming of flow portion 875 and a decrease of M-velocity lower than the specific M-velocity M.sub.*, i.e. M.sub.*>M.sub.804; at position 805 above concavity 874, the M-velocity M.sub.805 is minimal, thereby, providing the condition: M.sub.801>M.sub.802>M.sub.803=M.sub.*>M.sub.804>M.sub.805 at position 806, the flow convergence is accompanied by cooling of flow portion 875, a decrease of static pressure, and an increase of M-velocity, i.e. M.sub.805<M.sub.806; at position 807, the second critical condition point, where the varying value of the flow portion 875's cross-sectional area has the second local minimum, is designed to provide for that the M-velocity of flow portion 875 reaches the specific M-velocity M.sub.*, i.e. the condition M.sub.805<M.sub.806<M.sub.807=M.sub.* triggering the de Laval-like jet-effect is satisfied; and so, at positions 808 and 809, the flow divergence is accompanied by further cooling of flow portion 875, a decrease of static pressure, and an increase of M-velocity, i.e. M.sub.805<M.sub.806<M.sub.807=M.sub.*<M.sub.808<M.sub.809
Depending on profile 871, the M-velocity M.sub.809 of flow portion 875 at downstream position 809, may exceed the high M-velocity M.sub.801 of flow portion 875 at upstream position 801, so, wing 870 may be used as a jet-booster based on the de Laval-like jet-effect, operating at high velocities. In general, a use of a two-humped airfoil profile of a wing flying with the de Laval high M-velocities, in order to provide for the desired jet-effect, is yet one of the teachings of the present invention.

(375) In view of the foregoing description referring to FIG. 8d, it will be evident to a person skilled in the art that the effect of high M-velocity acceleration by the Coanda-jet-effect two-stage operation is applicable, for example, to high-speed aircraft design.

(376) In view of the foregoing description referring to FIGS. 6h, 7d, 8c, and 8d, it will be evident to a person skilled in the art that, considering a body, flying in air-environment with transonic, and/or supersonic, and/or hypersonic velocities, i.e. with high M-velocities higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, in contrast to a case, wherein a body having an arbitrary shape is decelerating when air-fluxes, which flow nearby around the body, become warmer and extra-warmed, a specifically-shaped body, having a two-humped airfoil profile providing for the two-stage operation of the Coanda-jet-effect, is accelerating, and air-fluxes, which flow nearby around the accelerating specifically-shaped body, become cooled and extra-cooled.

(377) Cascaded Jet-Boosters

(378) FIG. 9a is a schematic illustration of a sequential cascade of in-line arranged airfoil bodies 9011, 9013, 9014, 9015, and 9016, each in the shape of an elongated drop, exposed to oncoming wind 900 having the ambient M-velocity substantially lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. The shape of the elongated drops is optimized using the equation of M-velocity (6.13), basing on a specified thickness of a boundary layer over convex withers, as described hereinabove referring to FIGS. 8a and 8b. Points 9012 symbolize that the sequence of airfoil bodies may be much longer than shown. For simplicity, oncoming wind 900 is laminar. Trace a moving-small-portion 910 of ambient oncoming wind 900 passing positions 911, 9110, 912, 913, 9130, 914, 9140, 915, 9150, 916, 9160, and 917, considering a case when moving-small-portion 910 is subjected to the Coanda-jet-effect in an adiabatic process, defined by the partial pressure-c δP.sub.c, rather than affected by the skin-friction resistance, quantified by the difference (a.sub.w−a−δa). Moving-small-portion 910 at position 911 is yet to be subjected to the Coanda-jet-effect operation. I.e. at least the forward airfoil body 9011 meets moving-small-portion 910 with M-velocity, lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, and so body 9011 operates as a jet-booster based on the Venturi effect occurring in the adiabatic process in an imaginary tunnel adjacent to body 9011, as described above with reference to FIG. 8b. Further, moving-small-portion 910 is subjected to a cascaded operation of the Coanda-jet-effect in the adiabatic process by in-line arranged airfoil bodies 9011, 9013, 9014, 9015, and 9016, each of which operates as an elemental jet-booster, while meeting moving-small-portion 910 with M-velocity, lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. The cascaded operation of the Coanda-jet-effect results in aligning of the Brownian random motion of moving-small-portion 910's molecules with the surfaces of in-line arranged airfoil bodies 9011, 9013, 9014, 9015, and 9016, that is observed as an increase of the effective velocity of moving-small-portion 910, accompanied by moving-small-portion 910 temperature decrease, as moving-small-portion 910 sequentially passes positions 9110, 9130, 9140, 9150, and 9160, where flowing as ambient-adjoining convergent-divergent jetstreams. Thus, this results in an increase of moving-small-portion 910's kinetic energy at the expense of moving-small-portion 910's internal heat energy. Consider certain identical cross-sectional areas at positions 911, 912, 913, 914, 915, 916, and 917, marked by dashed ellipses, such that the Coanda-jet-effect operation influence is still perceptible within the marked areas. Considering flow velocities much lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, the effective velocity of flow crossing the marked areas at positions 911, 912, 913, 914, 915, 916, and 917 increases exponentially as the flow moves along the sequential cascade of in-line arranged airfoil bodies 9011-9016. For example, if the Coanda-jet-effect operation of each of airfoil bodies 9011-9016 in the adiabatic process provides an increase of the effective velocity of a flow portion, crossing the associated marked area, on 2%, then after 35 airfoil bodies 9011-9016 the effective velocity of the wind portion, crossing the marked area, is twice as high as the velocity of oncoming wind 900 yet to be subjected to the Coanda-jet-effect multi-stage cascaded operation. Consider a case, when the M-velocity M.sub.9130 of moving-small-portion 910, flowing as an ambient-adjoining convergent-divergent jetstream nearby the withers of airfoil body 9013, reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at position 9130. Triggering of the de Laval-like jet-effect causes the M-velocity M.sub.914 at position 914 to become higher than the specific M-velocity M.sub.*. The moving-small-portion 910 becomes cooled between positions 913 and 9130 and becomes extra-cooled between positions 9130 and 914. Running at airfoil body 9014, moving-small-portion 910 is subjected to the de Laval-like retarding-effect, such that the portion's M-velocity decreases down to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at position 9140 nearby the withers of airfoil body 9014, and becomes lower than the specific M-velocity M.sub.* at position 915. The moving-small-portion 910 becomes warmer between positions 914 and 9140 and becomes extra-warmed between positions 9140 and 915. Then moving-small-portion 910 is subjected to the de Laval-like jet-effect and the M-velocity increases again. Thus, when the sequence of airfoil bodies 9011-9016 is sufficiently long, the effective M-velocity of moving-small-portion 910 reaches the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} nearby the withers of airfoil bodies and varies around the value between the airfoil bodies. This is yet one more of the teachings of the present invention.

(379) In view of the foregoing description referring to FIG. 9a, it will be evident to a person skilled in the art that: in a more general case, when oncoming wind 900 is turbulent, such that moving-small-portion 910 comprises whirling groups of molecules, the Coanda-jet-effect multi-stage cascaded operation results in aligning also of the turbulent motion of the whirling groups of molecules with the surfaces of in-line arranged airfoil bodies 9011, 9013, 9014, 9015, and 9016, that is observed as an increase of the effective velocity of moving-small-portion 910, accompanied by moving-small-portion 910's inner turbulence decrease, as moving-small-portion 910, flowing as ambient-adjoining convergent-divergent jetstreams nearby around the withers of airfoil bodies 9011, 9013, 9014, 9015, and 9016, sequentially passes positions 9110, 9130, 9140, 9150, and 9160, correspondingly. Thus, this results in an increase of moving-small-portion 910's kinetic energy also at the expense of moving-small-portion 910's inner turbulent energy; the effect of M-velocity acceleration and stabilization by a multi-stage cascaded operation of the Coanda-jet-effect thereby reinforced multi-repeatedly is applicable, for example, to a high-speed long-train design; the effect of M-velocity stabilization is applicable, for example, to a flying train-like object, in particular, supplied with wings, which are not shown here, providing for a lift-force; an arrangement of airfoil bodies 9011, 9013, 9014, 9015, and 9016 along a smoothly curved locus, instead of the in-line arrangement, can be implemented; and the stabilized temperature difference between the extra-cooled airflow portions subjected to the triggered de Laval-like jet-effect and the extra-warmed airflow portions subjected to the triggered de Laval-like retarding-effect may be used to power a Peltier-element operating as a thermoelectric generator producing electricity.

(380) Reference is now made again to FIG. 9a, wherein now, all the in-line arranged airfoil bodies 9011, 9013, 9014, 9015, and 9016 are made from a conductive material, for simplicity, from a hypothetic super-conductor, wherein the sequence is exposed to electric flux 900. In view of the foregoing description referring to prior art FIG. 1f, the inventor points out that the effective electric flux crossing the marked areas at positions 911, 912, 913, 914, 915, 916, and 917 is self-increasing exponentially as flowing along the sequential cascade of in-line arranged airfoil conductive bodies 9011-9016 due to the electromagnetic jet-effect.

(381) FIG. 9b is a schematic illustration of a sequential multi-stage cascade of outer and nested airfoil rings 920, exposed to oncoming wind 921. Outer and nested airfoil rings 920 are formed by coiled-up walls having an actually-airfoil wing profile, similar, for example, to the profile of actually-airfoil wing 810, shown schematically in FIG. 8a. Thereby, outer and nested airfoil rings 920 have shapes of streamlined converging nozzles. The actually-airfoil wing profiles are optimized using the equation of M-velocity (6.13), basing on the specified thickness of a boundary layer over convex withers, as described hereinabove with the references to FIG. 8a. Points 929 symbolize that the sequence of outer and nested airfoil rings 920 may be much longer than shown. Airflow portions 922, flowing as ambient-adjoining convergent-divergent jetstreams, sliding outside of the sequential multi-stage cascade of outer rings 920, as well as wind portions 923, flowing and impacting inside of outer and nested airfoil rings 920, are subjected to the Coanda-jet-effect operation. Again, consider a case when airflow portions 922 and 923 are subjected to the Coanda-effect operation rather than to skin-friction resistance, thereby providing that each pair of outer and nested airfoil rings 920 operates as an elemental jet-booster. Airflow portions 922 and 923 join a cumulative outflow 924, wherein the Coanda-effect provides streamlines 925 forming an imaginary convergent-divergent nozzle downstream-behind the sequential multi-stage cascade of outer and nested airfoil rings 920. A sufficiently long multi-stage cascade of outer and nested airfoil rings 920 provides that the M-velocity of resulting cumulative outflow 924 reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the minimal cross-section 926 of the imaginary convergent-divergent nozzle and the de Laval-like jet-effect is triggered downstream-behind the minimal cross-section 926. Airflow portion 927 is expanded adiabatically; therefore, it is extra-cooled and extra-accelerated.

(382) A prolonged multi-stage cascade of outer and nested airfoil rings 920 may enable the M-velocity of airflow portions 922 to reach the specific M-velocity M.sub.* nearby the withers of airfoil outer rings 920. In this case, airflow portions 922 become subjected to the de Laval-like jet-effect, such that the effective M-velocity of airflow portions 922 is stabilized, as described hereinbefore with reference to FIG. 9a, considering a sequential multi-stage cascade of in-line arranged airfoil bodies, each having the shape of an elongated drop.

(383) FIG. 9c is a schematic illustration of a modified sequential multi-stage cascade of the outer and nested airfoil rings 920 of FIG. 9b into a pair of unbroken spirals shaped as the Archimedean screws 931 and 932 by helical coiling-up walls having airfoil profile 937, for example, similar to described above with reference to FIG. 8a. Airfoil profile 937, also shown separately above and to the left in an enlarged scale, is optimized using the equation of M-velocity (6.13), basing on the specified thickness of a boundary layer over convex withers, as described hereinabove with the reference to FIG. 8a, and taking into account an M-velocity range actually used for the spirals 931 and 932. Oncoming airflow portion 933 is yet to be subjected to the Coanda-jet-effect operation. Both: the sliding outside air sub-portions 934 flowing around and the inside impacting air sub-portions 935 flowing through the pair of spirals 931 and 932, are subjected to the Coanda-jet-effect operation, resulting in a converging flow when convergent flow sub-portions 934 and 935 laminarly join a resulting cumulative outflow 936. I.e. a fragment [for instance, one coil] of the pair of spirals 931 and 932 operates as an elemental jet-booster, and a longer fragment of converging spirals 931 and 932 provides higher acceleration of the airflow. Again, the Coanda-jet-effect provides streamlines 930 forming an imaginary convergent-divergent jet-nozzle downstream-behind the airfoil construction.

(384) Moreover, the two spirals 931 and 932 have opposite helical screwing rotations, namely: clockwise and inverse-clockwise, thereby providing a spatially varying cross-sectional area of gaps between the walls of the two spirals 931 and 932. The spatially varying cross-sectional area of the gaps provides a Venturi effect for velocities lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} and the de Laval-like jet-effect for velocities providing for reaching the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} at the critical condition point where the variable cross-sectional area of gaps becomes minimal. Sufficiently long converging spirals 931 and 932 provide acceleration of the airflow and stabilization of the effective velocity at the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} analogous to the cases described above with references to FIGS. 9a and 9b.

(385) In view of the foregoing description of FIGS. 9a, 9b, and 9c, it will be evident to a person skilled in the art that: One can implement many alterations, re-combinations and modifications of elemental jet-boosters, taught herein, without departing from the spirit of the disclosure that can be generalized as the following. A sufficiently long aggregation of elemental jet-boosters provides acceleration of an airflow portion, reaching the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, thereby triggering alternating the de Laval-like jet-effect and the de Laval-like retarding-effect, resulting in a stable alternation of the airflow portion effective M-velocity above and below the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} between the elemental jet-boosters; and The cumulative useful kinetic-power, including both: the originally brought kinetic-power and the acquired kinetic-power, provided by a multiplicity of elemental jet-boosters, aggregated into an adiabatic converging system, depends on a quality and quantity of the elemental jet-boosters and how the elemental jet-boosters are arranged and exploited. Moreover, it will be evident to a person skilled in the art that a sequential in-line multi-stage cascading of the elemental jet-boosters has an especial sense.
For example, consider an aggregation comprising N elemental jet-boosters exposed to an ambient flow and oriented such that each elemental jet-booster provides an increase of the effective velocity of the flow portion moving through a certain effective cross-sectional area, by a factor F, wherein F>1, and for simplicity and without loss of the explanation generality, consider a case of sufficiently low velocity of the ambient flow and assume that it is the same factor, independently of the elemental jet-boosters arrangement and exploitation. As well, for simplicity, consider the case, when the M-velocities of accelerated flow remain lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, thereby, justifying neglecting the flow density change in further approximate estimations. As the kinetic-power of a flow portion moving through a certain cross-sectional area is directly-proportional to the cross-sectional area and proportional to the third power of the flow portion velocity, each elemental jet-booster, when operating separately, launches a jetstream having the solitary useful kinetic-power, indicated by W.sub.1, proportional to the third power of the factor F, expressed by W.sub.1=W.sub.0×F.sup.3, where W.sub.0 is the originally brought ambient useful kinetic-power associated with the effective cross-sectional area of one elemental jet-booster.

(386) The solitary acquired kinetic-power ΔW.sub.1 is defined by the difference between the solitary useful kinetic-power W.sub.1 and the originally brought ambient useful kinetic-power W.sub.0, namely, ΔW.sub.1=W.sub.0×(F.sup.3−1); and so the aggregation, comprising N such elemental jet-boosters and thereby accelerating the flow portions, moving through N effective cross-sectional areas, results in the cumulative useful kinetic-power: indicated by W.sub.parallel, equal to W.sub.parallel=N×W.sub.1=N×W.sub.0×F.sup.3, wherein the cumulatively acquired kinetic-power ΔW.sub.parallel is defined as:
ΔW.sub.parallel=N×ΔW.sub.1=N×W.sub.0×(F.sup.3−1), in the case, when the elemental jet-boosters operate independently, that occurs, if the elemental jet-boosters are arranged in parallel, or if the elemental jet-boosters are arranged sequentially, but operating in a not adiabatic process, allowing for the solitary useful kinetic-power W.sub.1 to be consumed in parallel within or behind each elemental jet-booster and restored afore each next elemental jet-booster; or, alternatively, indicated by W.sub.sequential, equal to W.sub.sequential=W.sub.0×(F.sup.3).sup.N, wherein the cumulatively acquired kinetic-power ΔW.sub.sequential is defined as:
ΔW.sub.sequential=W.sub.0×[(F.sup.3).sup.N−N], in the case, when the elemental jet-boosters are arranged sequentially operating in the adiabatic process, and the consumption of the cumulative useful kinetic-power is allowed behind the downstream-end of the last elemental jet-booster only.
In an exemplary practical case, the effective velocity increase factor equals F=1.097. Then the following conditions become satisfied: the condition W.sub.sequential<W.sub.parallel is satisfied for N≤8; the condition W.sub.sequential>W.sub.parallel is satisfied for N≥9; the condition W.sub.sequential>2W.sub.parallel is satisfied for N≥13; the condition W.sub.sequential>3W.sub.parallel is satisfied for N≥15; and the condition W.sub.sequential>4W.sub.parallel is satisfied for N≥16.

(387) In view of the foregoing description of FIGS. 9a, 9b, and 9c, one of the primary teachings is that an artificial wind can be used for profitable harvesting of electricity. For example, one can: use a big-front ventilator [or group of ventilators], having 50%-net-efficiency, i.e. consuming electric-power W.sub.consumed and creating an originally incoming artificial airflow, bringing kinetic-power W.sub.income=0.5×W.sub.consumed, wherein the originally incoming artificial airflow has the front area A.sub.income of 4 times bigger than the effective cross-sectional area of an elemental jet-booster and has the effective velocity u.sub.income; implement a sequential multi-stage cascade, comprising N=15 elemental jet-boosters, each of which is characterized by the effective velocity increase factor F=1.097, such that altogether making an outflowing artificial jetstream, having velocity u.sub.jetstream=u.sub.income×F.sup.N [F.sup.N=1.097.sup.15≈4] and having the resulting effective front cross-sectional area A.sub.jetstream, decreased approximately 4 times relative to the area A.sub.income of originally incoming airflow [A.sub.income A.sub.jetstream=F.sup.N≈4]. Thus, the outflowing artificial jetstream brings the resulting useful kinetic-power W.sub.jetstream; estimated as:
W.sub.jetstream=[(u.sub.jetstream/u.sub.income).sup.3×(A.sub.jetstream/A.sub.income)]×W.sub.income; i.e. W.sub.jetstream=[4.sup.3/4]×W.sub.income=[16]×0.5×W.sub.consumed=8×W.sub.consumed;
and use a wind-turbine, producing electricity with 50%-net-efficiency, thereby, harvesting the useful electric-power W.sub.useful of 4 times higher than the consumed electric-power W.sub.consumed, namely,
W.sub.useful=0.5×W.sub.jetstream=0.5×(8×W.sub.consumed)=4×W.sub.consumed.
Wherein, the profit becomes greater than estimated, when the de Laval-like jet-effect is triggered. Thereby, in view of the foregoing description referring to FIGS. 9a, 9b, and 9c, it will be evident to a person skilled in the art that a profitable harvesting of electricity, using a jet-effect created by a multi-stage cascaded operation of the Coanda-jet-effect thereby reinforced multi-repeatedly, is feasible, for example, attaching sequentially arranged elemental jet-boosters to a sufficiently-long moving vehicle and using a wind-turbine, arranged behind the downstream-end of the last elemental jet-booster.

(388) In view of the foregoing description referring to FIGS. 9a, 9b, and 9c, the inventor points out that, when reaching the stabilized effective velocity equal to the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, the periodical local extra-acceleration and extra-retarding generate a forced extra-intensive elemental acoustic wave, wherein the distance between each two neighbor withers equals a half of wavelength of the forced extra-intensive elemental acoustic wave. Furthermore, the forced extra-intensive elemental acoustic waves are superposed in-phase thereby constituting the resulting extra-intensive acoustic wave as constructive interference. It will be evident to a person skilled in the art that the arrangement of airfoil bodies, either: 9011, 9013, 9014, 9015, and 9016 as shown in FIG. 9a; or a sequential multi-stage cascade of outer and nested airfoil rings 920 as shown in FIG. 9b; or a pair of unbroken spirals shaped as the Archimedean screws 931 and 932 by helical coiling-up walls having airfoil profile 937, as shown in FIG. 9c,
subjected to the generalized jet-effect (namely, the Coanda-jet-effect, the de Laval-like jet-effect, the de Laval-like retarding effect, and the enhanced waving jet-effect) and supplied by an acoustic detector capable of detection of the resulting extra-intensive acoustic wave power, can play a role of an electricity generator that, in the final analysis, produces the electric power at the expense of the warmth of the air.
Kinetic Enemy Accumulation, Conservation, and Use

(389) FIG. 9d illustrates schematically a circulating system 940 comprising a multi-stage cascade of many [8 shown] airfoil bodies 941 submerged in a fluid and arranged circumferentially. The rotation is in the inverse-clockwise direction as indicated by curved arrow 942.

(390) For simplicity, the shape and multi-stage cascading of airfoil bodies 941 are similar to the shape and multi-stage cascading of airfoil bodies 9011-9016 described above with reference to FIG. 9a, but now an asymmetry of shapes and attack angles of airfoil bodies 941 are such that the trajectories of flowing fluid portions 944 are aligned with the associated arc of circling.

(391) The fluid sub-portions 943, flowing around airfoil bodies 941, are subjected to the Coanda-effect and skin-friction; wherein when flowing adjacent to the withers of airfoil bodies 941, fluid sub-portions 943 are subjected to a cross-sectional varying, performing ambient-adjoining convergent-divergent jetstreams. Consider a case, when flowing fluid sub-portions 943 are subjected to the Coanda-effect operation rather than affected by the skin-friction resistance, and are, thereby, accelerated in the clockwise direction, forming flowing fluid portions 944 between circulating airfoil bodies 941. I.e. airfoil bodies 941 operate as elemental jet-boosters, analogous to the operation of airfoil bodies 9011-9016 (FIG. 9a).

(392) The sequential operation of the Coanda-jet-effect results in fluid portion 944's velocity distribution within cross-sections 9440, wherein the distribution occurs at the expense of fluid portion 944's temperature decrease. The term “local velocity” refers to the velocity of a flowing fluid sub-portion relative to the nearest flying body 941. The local velocity is directed substantially along a local sagittal axis, associated with the nearest flying body 941.

(393) The circulation creates a positive feedback loop, providing a cycling operation of the Coanda-jet-effect within an imaginary toroidal space having cross-sections 9440. The cycling operation of the Coanda-jet-effect results in further aligning of the Brownian random motion of fluid sub-portions 943 molecules with the profiles of airfoil bodies 941 that is observed as a further increase of the effective local velocity of circulating fluid sub-portions 943, accompanied by the fluid sub-portions 943 temperature further decrease. This provides further distribution of portions 944 local velocity and further acceleration of flowing fluid sub-portions 943 up to reaching the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} in the narrowest cross-section near the withers. The reaching of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} triggers alternating both the de Laval-like jet-effect and the de Laval-like retarding-effect, similar to that described hereinbefore with reference to FIG. 9a. Thus, the M-velocities of sub-portions 943 become stabilized at the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, and M-velocities of flowing portions 944 alternate above and below the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. Thus, the stabilized circulation of portions 944 within the imaginary toroidal space, having cross-sections 9440, may be interpreted as a conservation of the flowing portions 944 kinetic energy within the imaginary toroidal space. The accumulated and conserved kinetic energy of flow, indicated by K.sub.acc, is equal to K.sub.acc=0.5ρ.sub.effV.sub.toru.sub.eff.sup.2, where ρ.sub.eff is the effective density of circulating fluid, V.sub.tor is the volume of the imaginary toroidal space, and u.sub.eff is the effective local velocity of the circulating fluid, equal to u.sub.eff=M.sub.*×u.sub.sound, where u.sub.sound is the speed of sound in the fluid.

(394) In view of the foregoing description of FIG. 9d, it will be evident to a person skilled in the art that: a part of the accumulated kinetic energy K.sub.acc of flow can be consumed, for instance, in the form of a jetstream, outflowing from the imaginary toroidal space, that is not shown here; an arisen lack of the consumed kinetic energy of flow can be accumulated again up to the value K.sub.acc by sucking fresh portions of the surrounding fluid into the imaginary toroidal space; circulating multi-stage cascade 940 operates similarly to a long in-line multi-stage cascade of many airfoil bodies 9011-9016 described hereinbefore with reference to FIGS. 9a, 9b, and 9c, but now fluid portions 944 move along a curved and closed trajectory. Such an implementation of inverse circulation of flow relative to the direction of bodies 941s′ rotation is one of the teachings of the present invention as well; a fluid portion, circulating within the imaginary toroidal space and having the local velocity, static pressure, temperature, and density substantially distributed in cross-sections 9440, is subjected to inter-diffusion with the contacting fluid portion remained out of the imaginary toroidal space that results, in particular, in a caloric exchange between the fluid portions; and a circulating multi-stage cascade of elemental jet-boosters may function as a self-rotating warmth-to-motion engine.

(395) FIG. 9e is a schematic top-view of a stationary circumferential arrangement of many [42 shown] elemental jet-boosters 950, thereby embodying a vortex-generator, constructed according to the principles of the present invention and exposed to natural ambient wind 951, bringing fresh air portions storing both: the kinetic energy of flow [i.e. the kinetic energy the directional laminar motion, or, in terms of the kinetic theory of gas, the kinetic energy of the air molecules headway motion]; the kinetic energy of the Brownian random motion of air molecules [i.e. the inner heat]; and, in a more general case, the kinetic energy of whirling groups of air molecules [i.e. the turbulent energy].

(396) The center of the circle is marked by point 957. The elemental jet-boosters 950 have an effective height 9571 and the circumferential arrangement occupies a circle having effective overall diameter 9572. So, the circumferential arrangement overall shape is an imaginary cylinder having a base of effective overall diameter 9572 and a side of height 9571.

(397) For simplicity, the shown shape and multi-stage cascading of elemental jet-boosters 950 are similar to the shape and multi-stage cascading of airfoil outer and nested airfoil rings 920 described hereinbefore with reference to FIG. 9b. The airflow portions 953, flowing through the inner space of elemental jet-boosters 950, and portions 955 and 956 flowing as ambient-adjoining convergent-divergent jetstreams nearby around elemental jet-boosters 950, are subjected to the Coanda-jet-effect operation and, thereby converge. The circumferential arrangement provides that some elemental jet-boosters 950 are oriented to natural ambient wind 951, such that they operate as converging-nozzles; and some other elemental jet-boosters 950 are oriented to natural ambient wind 951, such that they operate as divergent nozzles. This asymmetry of elemental jet-boosters 950 orientations causes the oncoming airflow front to be non-uniform in direction and therefore has a tendency to flow around a side of the arrangement, as schematically shown by arrows 952. Considering flow M-velocities much lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, the multiplicity of elemental jet-boosters 950 causes accelerated wind sub-portions at position 954 to have local velocities, substantially higher than the velocity of natural ambient wind 951. This results in a circulation of airflow portions 953, 955, and 956 within an imaginary toroidal space, having effective overall diameter 9572 and a cross-section, marked by dashed ellipse 9573 having a diameter corresponding to effective height 9571. Circulating airflow portions 953, 955, and 956, become subjected to the Coanda-jet-effect circulating operation in a positive feedback loop, resulting in further aligning of the Brownian random motion of air molecules with the airfoil surfaces of elemental jet-boosters 950 that is observed as an increase of the effective local velocity of circulating airflow portions 953, 955, and 956, accompanied by the airflow portions temperature decrease. In a more general case, when airflow portions 953, 955, and 956 have inner turbulence, i.e. airflow portions 953, 955 and 956 comprise whirling groups of molecules, the Coanda-jet-effect multi-stage cascaded operation results in aligning also of the turbulent motion of the whirling groups of molecules with the airfoil surfaces of elemental jet-boosters 950, that is observed as an increase of the effective local velocity of airflow portions 953, 955, and 956, accompanied by the airflow portions inner turbulence decrease, as the airflow portions move within the imaginary toroid, sequentially passing elemental jet-boosters 950. Thus, this results in an increase of airflow portions 953, 955, and 956 kinetic energy also at the expense of airflow portions 953, 955, and 956 inner turbulent energy. The effective local velocity increase continues until reaching the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. Then the effective local velocity is stabilized triggering alternating both the de Laval-like jet-effect and the de Laval-like retarding-effect, as described hereinbefore with references to FIGS. 9a and 9d. In particular, an even number of jet-boosters 950 provides that the circulating airflow local velocities become steady-stately distributed in space. The circulating portions become cooled and extra-cooled, where the de Laval-like jet-effect is triggered, and become warmer and extra-warmed, where the de Laval-like retarding-effect is triggered.

(398) In view of the foregoing description of FIG. 9e, and referring to the description of FIG. 4, it will be evident to a person skilled in the art that: Airflow portions 953, 955, and 956, circulating within the imaginary toroidal space and having the local velocity, static pressure, temperature, and density substantially distributed in cross-sections 9573, are subjected to inter-diffusion with the contacting airflow portions remained out of the imaginary toroidal space. This results, in particular, in the caloric exchange between the airflow portions; The circumferential arrangement of many elemental jet-boosters 950 exposed to the natural ambient wind may function as a warmth-to-vortex/tornado generator that can power a rotor of an electricity generator; The circumferential arrangement of many elemental jet-boosters 950 exposed to the natural ambient wind accumulates and conserves the kinetic energy of flow K.sub.acc independently of the direction of horizontal wind, as well as independently of any variation in the natural gusty wind direction, and furthermore, independently of any variation of the natural gusty wind non-zero velocity; The stabilized temperature difference between the extra-cooled airflow portions, subjected to the triggered de Laval-like jet-effect, and the extra-warmed airflow portions, subjected to the triggered de Laval-like retarding-effect, may be used to power a Peltier-element operating as thermoelectric generator producing electricity, while the consumed heat power is restoring at the expense of the surrounding air caloric entering the imaginary toroidal space; The circumferential arrangement of many converging airfoil bodies operating as elemental jet-boosters 950 exposed to natural ambient humid wind can be used, for example, as an air cooler triggering condensation of water-vapor into water-drops that can be applied to water harvesting from humid air. Furthermore, it will be evident to a person skilled in the art that the condensation of water-vapor into water-drops is an exothermic process resulting in that the stabilized circulation of airflow has the stabilized temperature defined by the so-called “dew-point temperature” corresponding to the humidity of ambient wind; thus, the area, bordered by the circumferentially arranged elemental jet-boosters, performs an oasis of a stably-eddying windiness and refreshing coolness; and In a more general case, the circumferential arrangement of many converging airfoil bodies, operating as elemental jet-boosters 950 exposed to natural ambient wind 951, can enable rotations around the vertical axis through point 957 and power a rotor of an electricity generator. Alternatively, different arrangements of wind-turbines can be adapted to use the fast rotations of wind portions, again, while the consumed heat-power is restoring at the expense of the surrounding air caloric entering the imaginary toroidal space.

(399) In view of the foregoing description referring to FIGS. 9a, 9b, 9c, 9d, and 9e, it will be evident to a person skilled in the art that: one can configure many modifications of airfoil bodies operating as elemental jet-boosters, providing flow acceleration due to a multi-stage cascaded operation of the Coanda-jet-effect to reach the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} and, thereby, to trigger the de Laval-like jet-effect arising; and one can configure many modifications of elemental jet-boosters arrangements along smoothly curved loci, instead of the circumferential arrangement. The arrangement locus can be at least one of a line, an arc, a spiral of Archimedes, an outer helical outline of the Archimedean screw, a rounded contour, an ellipse, and a circumference.

(400) FIG. 9f is a schematic top-view of an adiabatic aerodynamic system 960, constructed according to the principles of the present invention, comprising: the stationary circumferential arrangement of many elemental jet-boosters 950, described above with reference to FIG. 9e having the same reference numerals 951, 952, 953, 954, 955, 956, 957, 9571, 9572, and 9573; and stationary airfoil wings 958, arranged within the mentioned imaginary cylinder having the basis of effective overall diameter 9572 and the side of height 9571.

(401) Airflow portions 959 are entrapped and drawn by stably circulating adjacent airflow portions 956, and so are stable-circulating as well.

(402) In one application, stationary airfoil wings 958 are configured and oriented to originate lift-forces under the influence of stable-circulating airflow portions 959.

(403) Alternatively, the airfoil wings 958 have symmetrical airfoil shape relative to a horizontal plane, and thereby do not originate lift-forces, but result in reactive thrust-forces directed along local sagittal axes, associated with nearest airfoil wings 958, due to the jet-effect as described hereinbefore referring to FIG. 8b, thereby enabling airfoil wings 958 rotations around the vertical axis through point 957. Wherein, if airflow portions 959 are subjected to the Coanda-effect operation rather than affected by the skin-friction resistance, then airfoil wings 958 rotation is in the inverse-clockwise direction, i.e. against the direction of airflow portions 959 rotation. This phenomenon is one of the teachings of the present invention as well.

(404) In view of the foregoing description referring to FIG. 9f, it will be evident to a person skilled in the art that: The lift-force, acting on wings 958, is independent of the direction of horizontal natural ambient wind 951, as well as independent of any variation in the natural gusty wind direction, and furthermore, independent of any variation of the natural gusty wind non-zero velocity; and it will be evident to a person skilled in the art that the lift-force, acting on wings, can be controlled by the airfoil wings configuration, arrangement, and orientation. An implementation of an adiabatic aerodynamic system, having no moving parts and providing for a stable and predictable lift-force generated at the expense of ambient air heat energy, is also one of the teachings of the present invention; Implementing an adiabatic aerodynamic system comprising a circumferential arrangement of many elemental jet-boosters, either a wide-front fluid flow or many fluid jetstreams, made artificially, can be used instead of the natural ambient wind; The principles, applied to the construction of adiabatic aerodynamic system 960, allow for a design of a flying-saucer. Wherein, in contrast to a principle of helicopter, where rotating wing-like blades interact with stationary air, here, stationary wings 958 interact with rotating airflow portions 959. As well, to provide a controlled maneuvering, adiabatic aerodynamic system 960 can be supplied with airfoil blades, similar to stationary wings 958, but having controllable degrees of freedom to be oriented asymmetrically relative to point 957, thereby, redirecting the stably circulating airflow portions out of the adiabatic aerodynamic system and allowing for a reactive push in any desired direction, as well as for stabilizing the flying-saucer position in atmosphere. Furthermore, the energy, conserved in the form of the stable-circulating airflow portions kinetic energy, allows for a fast maneuvering of the flying-saucer; and Adiabatic aerodynamic system 960, exposed to natural humid wind, can be adapted for the humidity condensation, and thereby, water harvesting from humid air. To estimate efficiency of the water condensation, consider a stationary circumferential arrangement of many elemental jet-boosters 950 exposed to natural ambient humid wind moving with velocity, indicated by u.sub.951 u.sub.951, and characterized by parameters of static pressure P.sub.951, temperature T.sub.951, density ρ.sub.951, and relative humidity h.sub.951, wherein in a normal exemplary case, the parameters are quantified as: u.sub.951=10 m/sec, P.sub.951=100 kPa, T.sub.951=298 K, ρ.sub.951=1.2 kg/m.sup.3, and h.sub.951=60%. The values of P.sub.951, T.sub.951, ρ.sub.951, and h.sub.951, correspond to absolute humidity H.sub.951=14 g/m.sup.3 and so-called “dew-point temperature”, equal to T.sub.dew=289K for the case. Consider an exemplary implementable case, when the effective overall diameter 9572 is equal to D.sub.9572=20.3 m, and the stabilized air motion with effective M-velocity, indicated by M.sub.9573, equal to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}, is through cross-sections 9573, having the effective diameter, indicated by d.sub.9573, equal to 0.5m. The volume of the imaginary toroidal space, having the effective overall diameter D.sub.9572 and the cross-sectional diameter d.sub.9573, is equal to V.sub.tor=π×D.sub.9572×0.25π×d.sub.9573≈12.5 m.sup.3, and the imaginary toroidal space bordering area, indicated by A.sub.tor, is equal to A.sub.tor=πD.sub.9572×πd.sub.9573≈100 m.sup.2. The imaginary toroidal space volume V.sub.tor comprises potentially yet to be condensed water-vapor, having mass M.sub.V, equal to M.sub.V=V.sub.torH.sub.951≈175 g. The acquired kinetic energy of the circulating airflow, K.sub.acquired, is defined as K.sub.acquired=0.5×V.sub.tor[ρ.sub.effu.sub.eff.sup.2−ρ.sub.951u.sub.951.sup.2], where the effective local velocity u.sub.eff of the airflow, circulating within the imaginary toroidal space, is quantified as u.sub.eff=M.sub.9573×u.sub.sound≈184 m/sec, and the effective density ρ.sub.eff interrelates with the stabilized dew-point temperature T.sub.dew, according to the Clapeyron-Mendeleev gas state law for an adiabatic process. Namely,

(405) $\begin{matrix} ρ_{eff} = {ρ_{951} (\frac{T_{dew}}{T_{951}})}^{\frac{1}{γ - 1}} \\ \approx 1.2 \times {(\frac{289}{298})}^{2.5} \\ \approx 1.1 kg / m^{2} \end{matrix}$
Thereby, the acquired kinetic energy K.sub.acquired, is estimated approximately as

(406) $\begin{matrix} K_{acquired} = 0.5 \times V_{tor} [ρ_{eff} u_{eff}^{2} - ρ_{951} u_{951}^{2}] \\ \approx 0.5 \times 12.5 \times [1.1 \times 184^{2} - 1.2 \times 10^{2}] \\ \approx 232 kJ . \end{matrix}$
To reach the dew-point temperature making the air portion saturated with humidity, the circulating humid air portion of the volume V.sub.tor must lose the internal heat energy, indicated by ΔU, estimated as: ΔU=ρ.sub.effV.sub.torR(T.sub.951−T.sub.dew)≈1.1×125×(8.31/0.0285)≈38 kJ.
The estimated value of the acquired kinetic energy K.sub.acquired is much greater than the value of internal heat energy loss ΔU, so after reaching the dew-point temperature, the energy difference (K.sub.acquired−ΔU)≈194 kJ goes to trigger the water condensation process. Condensation of water at the dew-point temperature requires a reducing of the saturated humid air portion's heat energy per unit mass on the value Λ.sub.water=2260 kJ/kg. Thereby, the estimated acquired kinetic energy of airflow K.sub.acquired potentially may be accompanied by the condensed water amount of M.sub.water=(K.sub.acquired−ΔU)/Λ.sub.water≈86 g. The value M.sub.water is substantially lesser than the estimated above mass M.sub.V of water-vapor that potentially could be condensed, so the water mass amount M.sub.water≈86 g is actually feasible for condensation.

(407) Further, a part of the circulating airflow can be permanently withdrawn in the form of outflowing jetstreams, for instance, under the influence of wings 958, arranged adjacent to the elemental jet-boosters 950 to redirect circulating airflow portions 959, resulting in drawing out air portions 956, 954, and 955 from the imaginary toroidal space. The outflowing jetstreams take away the acquired kinetic energy of circulating airflow K.sub.acquired. As the accumulated kinetic energy K.sub.acc of the airflow, circulating within the imaginary toroidal space, has a tendency to stabilization, so, an arisen lack of the accumulated kinetic energy of airflow K.sub.acc, caused by the withdrawn of the acquired kinetic energy of airflow K.sub.acquired, has a tendency to be reacquired again by sucking fresh portions of the surrounding air into the imaginary toroidal space and further, by an acceleration of the sucked fresh portions, increasing the sucked fresh portions local velocity up to the stabilized effective local velocity u.sub.eff=M.sub.*×u.sub.sound. The possible airflow discharge from and sucking into the imaginary toroidal space, indicated by Q.sub.fresh, is defined by the condition Q.sub.fresh>A.sub.toru.sub.951, as the ambient velocity u.sub.951 is substantially lower than the expected airflow local velocities at the borders of the imaginary toroidal space. Thus, the condition of the possible airflow discharge Q.sub.fresh is quantified as Q.sub.fresh>1000 m.sup.3/sec. The possible airflow discharge Q.sub.fresh is much greater than the airflow F.sub.9573 moving through cross-section 9573 of the imaginary toroidal space, estimated as F.sub.9573=0.25π×d.sub.573×u.sub.eff, and is sufficient to refresh the humid air in the imaginary toroidal space volume V.sub.tor several times per second, indicated by N.sub.refresh, defined and estimated as N.sub.refresh=Q.sub.fresh/V.sub.tor>80 sec.sup.−1. The intensity of water condensate harvesting, indicated by F.sub.condensation, is defined by the feasible condensed water amount M.sub.water≈86 g multiplied on the N.sub.refresh. Thus, the intensity of water condensate harvesting F.sub.condensation is estimated as:

(408) $F_{condensation} = N_{refresh} \times M_{water} > 6.88 \frac{kg}{\sec} \approx 413 kg / \min .$
The estimated intensity of water harvesting F.sub.condensation is at least of the same order of the value as a flux of water head discharging from a hose of a fire-extinguishing machine. Thereby, a stationary circumferential arrangement of many elemental jet-boosters 950 can be used for water harvesting from air for domestic and industrial needs, and, for example, attached to a helicopter, can be adapted for a fire-extinguishing.

(409) In view of the foregoing description referring to FIG. 9f, it will be evident to a person skilled in the art that airfoil wings 958, exposed to stably-circulating airflow portions 959 and enabling rotations around the vertical axis through point 957, may power a rotor of an electricity generator. Alternatively, the stabilized temperature difference between the extra-cooled airflow portions, subjected to the triggered de Laval-like jet-effect, and the extra-warmed airflow portions, subjected to the triggered de Laval-like retarding-effect, may be used to power a Peltier-element operating as thermoelectric generator producing electricity, while the consumed heat power is restoring at the expense of the surrounding air caloric entering the imaginary toroidal space. Thus, the acquired kinetic energy of airflow K.sub.acquired, refreshed N.sub.refresh times per second, may provide an acquired kinetic-power of airflow W.sub.acquired, defined as W.sub.acquired=N.sub.refresh×K.sub.acquired. Taking into the account the estimations made hereinabove, the possible acquired kinetic-power of airflow W.sub.acquired is estimated as: W.sub.acquired>18.56 MW. Thereby, a relatively compact stationary circumferential arrangement of many elemental jet-boosters 950 can be used for electric power producing for domestic and industrial needs.

(410) In view of the foregoing description referring to FIGS. 9a, 9b, 9c, 9d, 9e, and 9f, it will be evident to a person skilled in the art that the circumferential arrangement of many elemental jet-boosters exposed to moving seawater can be adapted for electricity harvesting from the seawater motion.

(411) In view of the foregoing description referring to FIGS. 9e and 9f, it will be evident to a person skilled in the art that the circumferential arrangement of many converging airfoil bodies operating as elemental jet-boosters 950 exposed to either natural or artificial wind can be used, for example, as a wind tunnel in an aerodynamic laboratory, providing a stable spatial distribution of the wind velocities.

(412) In view of the foregoing description referring to FIGS. 9d, 9e, and 9f, the inventor points out that, when the circumferential arrangement is regularly equidistant and when portions 955 and 956 are reaching the stabilized effective M-velocity equal to the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} near withers of the circumferentially arranged elemental jet-boosters 950, the periodical local extra-accelerations and extra-retarding generate a forced extra-intensive and in-phase superposed elemental acoustic waves, wherein the distance between each two neighbor withers equals a half of wavelength of the forced extra-intensive elemental acoustic wave.

(413) The inventor points out that each of elemental jet-boosters 950 acts as a source of an extra-intensive peculiar shock-like acoustic wave characterized by the peculiar frequency and wavelength, while each pair of the neighbor elemental jet-boosters 950 acts as a source of the extra-intensive forced elemental acoustic wave characterized by the forced frequency and wavelength. The forced extra-intensive elemental acoustic waves are superposed in-phase thereby constituting the resulting extra-intensive acoustic wave as constructive interference with respect to the system of coordinates linked to the whirling flow portions.

(414) It will be evident to a person studied the present invention that: The circumferential arrangement of elemental jet-boosters 950, subjected to the generalized jet-effect (namely, the Coanda-jet-effect, the de Laval-like jet-effect, the de Laval-like retarding effect, and the enhanced waving jet-effect) and supplied by an acoustic detector capable of detection of the resulting extra-intensive acoustic wave power, can play a role of an electricity generator that, in the final analysis, produces the electrical power at the expense of the warmth of the air; and The whirling of air portion with the effective M-velocity equal to the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} once becoming stabilized, continues self-supporting even in the absence of the circumferential arrangement of elemental jet-boosters 950. For instance, the well-known Great Red Spot of Jupiter is such a stabilized tornado. Furthermore, constructive interference of extra-intensive peculiar shock-like acoustic waves, characterized by the peculiar wavelength, can be observed as a regular polygon built-in into the stabilized whirling, where the side of the polygon is equal to the peculiar wavelength. For instance, the well-known Saturn's Hexagon is such a stabilized and stably whirling interference map.
Improved Wind-Turbine

(415) FIG. 9g is a schematic drawing of modified improved wind-turbine 9.0, constructed according to the principles of the present invention to operate under relatively fast airflow 9.1 for producing the electric power at the expense of the warmth of relatively fast airflow 9.1.

(416) Modified improved wind-turbine 9.0 comprises: axle 9.2 oriented along sagittal axis 9.21 codirected with fast airflow 9.1, identical asymmetrical biconvex actually-airfoil blades 9.3, attached to axle 9.2; and an engine [not shown here], capable of transforming the power of the forced mechanic rotational motion 9.4 of axle 9.2 into the electric power.

(417) The primary feature, making the modified wind-turbine 9.0 practically implementable and extremely efficient, is the specifically configured and so specifically functioning biconvex actually-airfoil blades 9.3. Namely, in contrast to standard wind-turbines having standardly shaped blades configured to be subjected to impacting by an incoming airflow that, in particular, results in the airflow turbulence, retarding, and warming, the modified improved wind-turbine 9.0 has asymmetrical biconvex wing-like actually-airfoil blades 9.3: having opposite convex sides 9.31 and 9.32 with withers differing in convexity and being oriented along and so adapted to the incoming fast airflow jetstream 9.11 headway motion.
Thereby configured and oriented blades provide the so-called zero attack angle: to exclude or at least to minimize the impact by the incoming fast airflow jetstream 9.11, but to provide an interaction with the fast airflow jetstream 9.11 by the Coanda-jet-effect only, thereby resulting in an acceleration and cooling of outflowing jetstream 9.6 and resulting in lift-forces, acting on identical biconvex actually-airfoil blades 9.3 and being disbalanced because of the aligned asymmetry of the identical biconvex airfoil blades.
In this case, the axle 9.2 rotational motion, shown by the curved arrow having numeral 9.4, is caused by the cumulative resulting lift-force. Take note again, that the Coanda-jet-effect is triggered by the airflow kinetic-power and is actually powered at the expense of the airflow warmth but not at the expense of the incoming fast airflow jetstream 9.11 kinetic-power; contrariwise, the kinetic-power of outflowing jetstream 9.6 is increased or at least not decreased with respect to the oncoming fast airflow 9.1. Thus, in contrast to the standard wind-turbines, the proposed improved wind-turbine 9.0 is specifically characterized: by the mechanism of operation, that is the Coanda-jet-effect but not the impact; and by the power source of operation, that is the warmth but not the kinetic power of airflow.

(418) Also, in contrast to a kind of the standard wind-turbines having wing-like blades moving around a vertical axis, the proposed improved wind-turbine 9.0 is specifically characterized by the excluding of varying poorly-streamlined positions of the wing-like blades.

(419) As well, in contrast to the standard wind-turbines, a productivity of the proposed improved wind-turbine 9.0 is defined by the area of the biconvex airfoil blades rather than by a so-called “swept area”, namely, the produced electric power due to the Coanda-effect is specified as proportional to the biconvex airfoil blades area, i.e. the productivity can be increased substantially for a given swept area.

(420) In view of the foregoing description referring to FIG. 9g, it will be evident to a person skilled in the art that modified improved wind-turbine 9.0 comprising: the biconvex airfoil blades, having a wing-like sectional contour with a longer so-called chord of wing, and/or an increased quantity of the biconvex airfoil blades,
both circumstances provide for enforcing of the desired Coanda-jet-effect. As well, it is self-suggested a sequential in-line arrangement of a multiplicity of modified improved wind-turbines 9.0 one downstream after another (optionally, alternatingly differing in asymmetry to become forcedly rotated alternatingly clockwise and inverse-clockwise, correspondingly), each separately and all together efficiently operating within the given swept area.

(421) Moreover, at least one of the profiles 9.31 and 9.32 is implemented to provide the de Laval enhanced jet-effect, when the incoming fast airflow jetstream 9.11 is flowing with a de Laval M-velocity and so a portion of jetstream 9.11 is reaching the specific M-velocity nearby the withers of the asymmetrical biconvex actually-airfoil blades 9.3. In this case, the extra-efficiency of the modified improved wind-turbine is expected.

(422) Furthermore, optionally, sides 9.31 and 9.32 differ in shape such that one of the sides has one convex withers and the opposite side has a two-humped airfoil profile providing for the two-stage operation of the Coanda-jet-effect as described hereinabove with the reference to FIG. 8d. Such asymmetrical blades, when exposed to oncoming fast airflow 9.1 moving with a high M-velocity, higher than the specific M-velocity, become subjected, on the one hand, to the de Laval retarding effect, and on the other hand, to the de Laval enhanced jet-effect. This provides for extra-increased lift-forces rotating axle 9.2. In this case, the extra-efficiency of the modified improved wind-turbine is expected in a wide range of velocities.

(423) FIG. 9h is a schematic drawing comprising the side view and front view of an improved wind-turbine 9.7, constructed according to the principles of the present invention to operate under relatively fast airflow 9.70 for producing the electric power at the expense of the warmth of relatively fast airflow 9.70. In relation to all the principal features, the improved wind-turbine 9.7 is similar to the improved wind-turbine 9.0, described hereinabove referring to FIG. 9g, but now, referring to the aforementioned optional diversity of the principal features implementation, the biconvex actually-airfoil blades, which having opposite at least partially convex sides 9.71 and 9.72 with withers differing in convexity, are further curved and screwed to optimize a suppression of turbulence as well as are cascaded one downstream after another to provide a multi-stage repeated operation of the Coanda-jet-effect thereby contributing to the desired cumulative lift-force to rotate axle 9.73.

(424) In view of the foregoing description referring to FIGS. 9g and 9h, it will be evident to a person skilled in the art that modified improved wind-turbine 9.0 or 9.7, when attached to a flying aircraft, is capable for efficient harvesting of the electric power from the ambient air warmth.

(425) Furthermore, in view of the description expound hereinabove with references to FIGS. 5i, 5j, 5k, 9a, 9b, 9c, 9d, 9e, and 9f, the inventor points out that the mentioned multiplicity of modified improved wind-turbines 9.0 or 9.7, arranged sequentially one downstream after another [not shown here], results in generation of acoustic waves accompanied by extraction of the internal heat energy of ambient air in favor for the wave power due to the enhanced waving jet-effect. Thus, a system, comprising the arrangement and a detector of the acquired wave power, has an additional degree of freedom to increase the efficacy of the producing of electricity.

(426) In view of the foregoing description referring to FIGS. 9g and 9h in combination with the foregoing description of subparagraphs “Point of San” and “Flying Bird”, both with the reference to prior art FIG. 1i, it will be evident to a person skilled in the art that the construction of modified improved wind-turbine 9.7, when having a controllable speed of the axle 9.73 rotation adapted to the velocity of oncoming airflow 9.70 to keep the airflow remaining laminar, provides a controllable net jet-thrust against the oncoming airflow 9.70 and so becomes applicable as a kind of jet-engine for a controllable and substantially noiseless flying.

(427) A Jet-Transformer

(428) FIG. 9i is a schematic illustration of a concept to transform the ambient warmth into electricity. The concept is embodied as a jet-transformer 9.80 comprising: a vertically oriented specifically shaped pipe 9.81 having the optimized convergent-divergent inner tunnel, described hereinabove in sub-paragraph “Convergent-Divergent Jet-Nozzle” with reference to FIG. 6a, at least one laminar flow maker 9.82, conceptually, having a geometry of convex-concave corpus 9.821 supplied by a heater 9.822, i.e. being designed as the convex-concave corpus 512 described hereinabove with reference to FIG. 5e, and at least one improved wind-turbine 9.83, designed as the improved wind-turbine 9.7 described hereinabove referring to FIG. 9h,
the all, constructed according to the principles of the present invention.

(429) The specifically shaped pipe 9.81 is elevated above the ground to allow for the ambient air 9.841 entering the optimized convergent-divergent inner tunnel from below. The heater 9.822 supplies the heat energy to a fluid portion adjacent the focus of the parabolically-concave surface 9.823 of the convex-concave corpus 9.821, thereby, on the one hand, to trigger the Archimedes upward-vectored buoyant force lifting the heated fluid potion and, on the other hand, to align the airflow 9.842 upward along the vertical axis 9.851. The upward airflow 9.842 is relatively slow and substantially-laminar. The optimized convergent-divergent inner tunnel is designed according to the equation of M-velocity (6.13) to provide for substantial suppression of jumps of the air thermodynamic parameters and, thereby, to provide for the substantial acceleration of the airflow 9.842, laminarly and so noseless streaming upward. So, the heating triggers the upward motion of air, and, in turn, the fluid motion itself triggers the convective acceleration as the airflow moves through the narrowing cross-section of the optimized convergent-divergent inner tunnel. Considering: the ambient temperature above the exhaust 9.854 equal T.sub.e, the temperature near the level 9.852 equal T.sub.0, and the temperature near the narrow throat 9.853 equal T.sub.*,
equation (7.1c), described hereinabove referring to FIG. 7a, says that: on the one hand, to obtain the de Laval jet-effect for air utilizing the optimized convergent-divergent inner, one must provide the ratio T.sub.0/T.sub.* at least of 1.2; and on the other hand, to accelerate an air portion up to the velocity of sound, one must provide the ratio T.sub.0/T.sub.e at least of 1.7.

(430) Hence, providing the heating of air near the level 9.852 up to about the temperature 234° C. only, the condition of the enhanced de Laval jet-effect becomes satisfied, in turn, providing that the relatively low heat power, supplied by heaters 9.822, triggers the enhanced de Laval jet-effect transforming the warmth of the moving airflow into the acquired kinetic power of the airflow.

(431) The energy E.sub.0, necessary for warming 1 cube meter of air from the temperature 25° C. up to the temperature 234° C., is estimated as E.sub.0=ρVC.sub.V(T.sub.0−T.sub.e), where V is the volume of 1 cube meter, ρ is the air density, ρ≈1.2 kg/m.sup.3, C.sub.V is the air heat capacity, C.sub.V≈0.72 kJ/(kg.Math.K), thereby, E.sub.0≈1.2×1×0.72×(234−25)≈180 kJ.

(432) As the mentioned assumed condition allows to accelerate the airflow portion 9.854 up to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} near the narrow throat 9.853 and to accelerate the airflow portion 9.854 up to almost the speed of sound (i.e. the exhaust M-velocity is of M.sub.e≈1), then: the acquired kinetic energy, K.sub.e, of the outflowing airflow portion 9.854, which (the acquired kinetic energy K.sub.e) is specified as the difference between bringing heat energies, equals K.sub.e≈n×(T.sub.0−T.sub.e)×R, where n is number of moles in the considered 1 cube meter of air, n≈44.64, and R is the specific gas constant, approximated for the air by R=287 J/(kg.Math.K), i.e. K.sub.e≈44.64×209×287≈2,677 kJ, that, in turn, says that the acquired kinetic energy K.sub.e may exceed the consumed energy E.sub.0 at least at subsonic velocities by the factor of 15; and the acquired kinetic energy, K.sub.*, of the airflow portion 9.854, when crossing the narrow throat, equals K.sub.*≈n×(T.sub.0−T.sub.*)×R≈764 kJ, thereby showing that the acquired kinetic energy K.sub.* may exceed the consumed energy E.sub.0 by the factor of 4.24.

(433) It will be evident to a commonly educated person that, if not to use the optimized convergent-divergent inner tunnel, designed according to the equation of M-velocity (6.13), the mentioned effective conversion of the airflow heat energy into the airflow kinetic energy is impossible because of originated turbulences and Mach waves, both accompanied by noise and energy dissipation back to the air warmth.

(434) The improved wind-turbine 9.83 meets the upping laminar airflow and provides for the production of electricity neither retarding the upward airflow and nor distorting the upward airflow laminarity as described hereinabove referring to FIGS. 9g and 9h. The inventor points out again that the improved wind-turbine 9.83 harvests electric power at the expense of the airflow warmth but not from the airflow kinetic power, wherein the increased kinetic power of the airflow plays the role of an enforced trigger of the lift-force rotating the improved wind-turbine. Moreover, optionally, in-line arranged several improved wind-turbines 9.83 provide for a multi-stage repeatedly harvesting of electricity from the same airflow portion.

(435) Method for Computational Analysis

(436) FIG. 10 is a schematic block-diagram 1000 of a method for computational fluid dynamics numerical analysis, based on the principles of the present invention.

(437) Block 1010 represents standard pre-processing comprising a defining the calculation space and mesh for the space quantization.

(438) Block 1020 represents the processing itself, i.e. the algorithm calculating numerically the spatial distribution of the velocity-vector (three components), static pressure, temperature, and density (total six components), programmed according to the principles of the present invention, and applying a computational analysis basic principle, comprising a digital approximation of a space, comprising the flowing fluid, by a virtual spatial mesh partitioned into non-overlapping quantization cells bordered by imaginary boundaries.

(439) The processing is such that the calculated spatially distributed values (i.e. the values calculated for the non-overlapping quantization cells) are satisfied, on the one hand, to suggested modified equations of fluid motion (5.6), (5.7), (5.9) having an exact solution, and, on the other hand, to the gravitational, thermodynamic, and kinetic theory laws represented by specified equations (5.2), (5.3), (5.4), (5.5), and (5.8), wherein the adequacy of the solution is confirmed by the Bernoulli theorem, equation (5.10).

(440) Block 1030 represents the standard post-processing procedure for the solution filing and visualization.

(441) Thereby, one can implement blocks 1010, 1020, and 1030 as a computer program product comprising a computer usable medium having computer readable code and instructions embodied and stored therein for execution on a general purpose computer. The code and instructions, when executed by the computer, cause the computer to perform the method for computational fluid dynamics.

(442) FIG. 11 comprises Table-1 showing several equations: On the one hand, classical, derived from the Euler theory in frames of the continuum mechanics and thermodynamics; and On the other hand, specified in the present invention, derived basing on the principles of the kinetic theory of matter.

(443) The inventor points out that: The difference between the expressions of the equations of fluid motion: classical and specified, is predetermined by the difference of definitions of the inner static pressure and density. Namely, in the continuum mechanics, the static pressure is defined as an integrated mechanical parameter characterizing the force acting on a wall, wherein the static pressure and mass density are inter-independent; and, in the present invention, the interrelated inner static pressure and mass density, both are defined from the point of view of the kinetic theory of matter applied to molecular fluid; The generalized adiabatic compressibility parameter, indicated by γ, generalizes the adiabatic compressibility-constant, indicated by j, by taking into the consideration that the adiabatic compressibility properties are predetermined by both: the adiabatic compressibility-constant and the van der Waals constants; The equation of M-velocity (6.13) differs from the classical equation (1) derived basing on the Euler equation defined in frames of the continuum mechanics; and The specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} differs from the M-velocity of 1 Mach, which plays the role of the specific M-velocity in the classical aerodynamic theory of the de Laval nozzle.

(444) The method, based on the kinetic theory of matter, provides the modified equations of fluid motion, thereby, reducing a sense of one of the Millennium Goals to solve the problem of the Navier-Stokes equation solution existence. The direct application of the disclosed method for computational analysis is the analysis of the flow motion, including a local oscillation motion of fluid, which is manifested as a wave propagating through a molecular fluid with the wave number interrelated with the velocity of sound in the molecular fluid.

(445) Considering a fluid as a substance composed of randomly moving molecules, the method enables applications optimization, the physical essence of which is to bring in an asymmetrical influence into the molecular fluid, and, thereby, to originate a motion of molecules in a prevalent direction. For instance, such an asymmetry is provided by a structured and heated surface thereby repelling the molecular fluid in a prevalent direction, or by a structured naturally hydrophobic surface contacting with water, or by a structured and electrically charged surface interacting with an ionized fluid, or by an airfoil body moving relative to the molecular fluid and thereby acting on the molecular fluid by the Coanda-effect.

(446) The method enables optimized designs of apparatuses for electricity harvesting from the molecular fluid heat energy, providing a positive net-efficiency. The method, accompanied by novel teachings, allows for optimized designs of engines having novel functionalities, for examples, such as: Fluid-repellent jet-gears, described with references to FIGS. 5d, 5e, 5f, 5g, 5h, 5i, 5j, and 5k, which, when submerged in ambient fluid, originate a circulating and/or headway self-motion at the expense of the ambient fluid warmth; as well, creating a controllable omniphobic repellency using heating elements, one can originate a fluid-repellent jet-gear motion with a high net-efficiency, even higher than 100%, again, at the expense of the ambient fluid warmth; An ice-maker comprising either hydrophobic jet-gears and comprising a generator, in the final analysis, transforming the heat into electricity, and thereby cooling and freezing water and so harvesting potable water (i.e. ice), as described with references to FIG. 5g; A capillary tube having inner saw-like hydrophobic walls, described with reference to FIG. 5d, which, when filled with water, provides the water transportation; Referring to FIG. 5i comprising a spiral, having a form of the Archimedean screw and having a hydrophobic surface, a mechanism, synthesizing a natural protein, or more fundamentally, of ribonucleic acid (RNA) molecules, hypothetically, can be specified and implemented artificially; An electrically charged propeller-like jet-gear, described with references to FIG. 5h, which, when submerged in an ionized gas or liquid, provides a motion of the jet-gear at the expense of the ionized fluid's warmth; A motionless gravity-jet engine, described with references to FIG. 5n, which, when operating in the gravitational field, is capable of a transformation of water heat energy into the kinetic energy of water jetstream moving upward, which, when becomes reincarnated into a waterfall, allows for the electricity harvesting and wherein reverting a falling water portion back into a container; An enhanced transformer, described with references to FIG. 5o, which, when transforming an alternating voltage and current, is capable of a transformation of the electromagnetic gas hidden energy into the useful electric energy, i.e., in the final analysis, allows for the electricity harvesting from the ambient temperature; A generalized generator for producing a useful-beneficial power, described with reference to FIG. 5m, which, when concretized as a fluid flow accelerator, provides for the useful-beneficial power harvesting from the fluid warmth in an adiabatic process due to the Coanda-jet-effect; and when concretized as a waves synchronizer, provides for the useful-beneficial power harvesting using constructive interference due to the waving jet-effect; An optimized convergent-divergent tunnel, described with reference to FIG. 6a, which, when triggering the de Laval enhanced jet-effect, provides conditions to acquire a kinetic power and/or to harvest electricity from air warmth with a positive net-efficiency; A two-stage convergent-divergent jet-nozzle described with reference to FIG. 6h, which, when exposed to transonic and/or supersonic and/or hypersonic flow, in contrast to the known phenomenon of the incoming flow warming and retarding, provides the incoming flow cooling and acceleration; An airfoil flying capsule having an optimized single-stage or two-stage convergent-divergent tunnel, which, when moving in air, is capable of transforming the air warmness into a useful jet-thrust; An improved propeller, preferably composed of many small propellers distributed in space, which focuses and/or defocuses sub-portions of air, thereby forming a cumulative blowing and/or sucking jetstream, correspondingly, wherein the jetstream has an optimally-variable cross-section providing for the critical condition, triggering the de Laval-like enhanced jet-effect; An improved wind-turbine configured: to exclude or at least to minimize the impact by incoming airflow, but to trigger at least one of the Coanda-effect and the de Laval enhanced jet-effect, both having the jet-effect nature, and, in the final analysis, to produce the electric power at the expense of the airflow warmth but not at the expense of the airflow kinetic-power; and An adiabatic aerodynamic system described with reference to FIGS. 9e and 9f, comprising a stationary circumferential arrangement of many elemental jet-boosters, that is capable of acquiring the kinetic energy of circulating airflow at the expense of the ambient air heat energy, further, to accumulate and conserve the airflow kinetic energy in a form of stably-circulating airflow. Wherein the adiabatic aerodynamic system, exposed to the natural ambient wind, accumulates and conserves the kinetic energy of the stably-circulating airflow independently of weather conditions, namely, independently of the direction of horizontal wind, as well as independently of any variation in the natural gusty wind direction, and furthermore, independently of any variation of the natural gusty wind non-zero velocity. This provides at least the following novel applications: The adiabatic aerodynamic system can operate as vortex-generator of an electro-station, providing for electric power harvesting from the warmth of natural air. Furthermore, it is found that the adiabatic aerodynamic system exposed to an artificial wind, made by consuming either a power of burned fuel or an electric power, under certain conditions, can convectively accelerate the wind at the expense of the airflow warmth thereby providing an acquired kinetic power of airflow being higher than the power consumed for the making of artificial wind; The adiabatic aerodynamic system can be used as an engine, powering a flying-saucer of high mobility, wherein, in contrast to a principle of helicopter where rotating wing-like blades interact with stationary air, here, just stationary wings of the flying-saucer interact with the stably-circulating airflow; The adiabatic aerodynamic system can be adapted for condensation of natural air humidity, wherein, considering a relatively compact adiabatic aerodynamic system, an estimated intensity of the water harvesting is at least of the same order of the value as a flux of water head discharging from a hose of a fire-extinguishing machine; and The adiabatic aerodynamic system, made in large-scale, can be used as a windbreak of an oasis of a stably-eddying windiness and refreshing coolness.

(447) The method enables a technology to control the transformation of the ambient surroundings (for instance, air and/or water) warmth into a directional motion of the fluid providing for a renewable cycle, comprising: transformation of the flowing fluid heat-power into acquired kinetic-power of an originated jetstream; conversion of the jetstream kinetic-power into useful electric-power; and consumption of the electric-power, in the final analysis, inevitably dissipating back into the warmth of surrounding matter.

(448) The method, accompanied by novel teachings, allows for a proper analysis of waves as a process of an interaction between an oscillator, supplying power to the ambient medium, and the ambient medium itself; wherein the process is accompanied by an adiabatic process of the waves propagation and interference.

(449) The method enables optimized designs of controllable apparatuses having novel functionalities for a useful-beneficial power harvesting (for instance, harvesting of electricity from the molecular fluid heat energy using constructive interference of energetically inter-independent acoustic waves). Furthermore, applications, providing for a use of constructive interference of acoustic waves, are hypothetically translatable to applications, providing for a use of constructive interference of electromagnetic waves.

DRAWINGS

(450) It should be understood that the sketched exemplary embodiments are merely for purposes of illustrating the teachings of the present invention and should in no way be used to unnecessarily narrow the interpretation of, or be construed as, being exclusively definitive of the scope of the claims which follow. It is anticipated that one of skill in the art will make many alterations, re-combinations, and modifications of the embodiments taught herein without departing from the spirit and scope of the claims.

Generalized jet-effect and enhanced devices

Assignee

Inventors

Cpc classification

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F01D5/141

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F05D2220/32

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F15D1/0015

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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B01D53/265

PERFORMING OPERATIONS; TRANSPORTING

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Y02T50/60

GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS

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H01F30/16

ELECTRICITY

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Y02E10/72

GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS

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F03D1/0633

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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H02K7/183

ELECTRICITY

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F02K3/04

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02K99/00

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F15D1/12

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02C7/141

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F03D1/0625

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02K7/12

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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H10N10/10

ELECTRICITY

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F03B1/00

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

International classification

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F15D1/12

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02K99/00

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F03D1/06

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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B01D53/26

PERFORMING OPERATIONS; TRANSPORTING

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F01D5/14

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02C7/141

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

Classification Explorer

F02K7/12

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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F02K3/04

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING