Apparatuses Based on Jet-Effect and Thermoelectric Effect

Abstract

The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

Claims

1. An acoustic thermoelectric device [5Q.DEVICE, 5R.DEVICE] comprising: a multiplicity of elemental acoustic thermoelectric devices [5P.0] aggregated as a whole in a matrix; and a controller-dispatcher; wherein each of the elemental acoustic thermoelectric devices comprising: a thermoelectric element having two opposite sides: first and second, faced to two opposite directions away each from other, wherein the first side is supplied with a thermoconductive bus [5P.7A, 5P.7B] being thermally in contact with a first body, and the second side is supplied with a thermoconductive bus [5P.5A, 5P.5B] being thermally in contact with a second body, wherein: said first body is at least one of a first solid body, a first portion of ambient fluid, and a first portion of a boundary layer; and said second body is at least one of a second solid body, a second portion of the ambient fluid, and a second portion of a boundary layer; and an individual controller [5P.8A, 5P.8B] having an integrated circuit, wherein the integrated circuit [5P.B1A, 5P.B10.A, 5P.8B, 5P.B10B] is supplied with at least one of: a controllably manipulatable source of electromotive force (emf) or generator [5P.B2A, 5P.B20A] of alternating electric current, wherein the alternating electric current is characterized by an alternation frequency being in a range of at least one of audible sound and ultrasound frequencies, to provide a capability of operating of the elemental acoustic thermoelectric device as a fluid pusher-off in a mode of sound launching when: the elemental acoustic thermoelectric device is submerged in the ambient fluid such that the first side is thermally in contact with the first portion of the ambient fluid and the second side is thermally in contact with said second body, and the controllably manipulatable source of emf or generator generates the alternating electric current; thereby, the capability of operating of the elemental acoustic thermoelectric device as the fluid pusher-off is provided by electric current changes originated by the controllably manipulatable source of emf or generator and, in turn, by arising temperature changes in the first portion of the ambient fluid due to the Peltier effect, wherein the arising temperature changes resulting in jet-effect motion of the first portion of the ambient fluid and; an electric circuit [5P.B10.A, 5P.B10B] capable of detecting an induced alternating electric current to provide a capability of operating of the elemental acoustic thermoelectric device as a fluid motion-sensor in a mode of sound detection when: the elemental acoustic thermoelectric device is submerged in the ambient fluid such that the first side is thermally in contact with the first portion of the ambient fluid and the second side is thermally in contact with the second body, and the first side of the elemental acoustic thermoelectric device is exposed to an impacting acoustic wave propagating in the ambient fluid wherein the impacting acoustic wave is characterized by an amplitude interrelated with an amplitude of changes in temperature of the first portion of the ambient fluid and by a frequency being in a range of at least one of audible sound and ultrasound frequencies; thereby, the capability of operating of the elemental acoustic thermoelectric device as the fluid motion-sensor is provided by temperature changes originated by a motion of the first portion of the ambient fluid and, in turn, origination of electric current in the electric circuit due to the Seebeck effect; and an individual sensor-controller capable of both: detecting an induced alternating electric current due to sudden changes in temperature of the first side being thermally in contact with the first portion of the boundary layer; and controlling by the manipulatable source of emf; to provide a capability of operating in a mode of boundary layer control, when: the first side is thermally in contact with the first portion of the boundary layer and the second side is thermally in contact with the second body, and a headway velocity of the boundary layer is either low-subsonic, or high-subsonic, or transonic, or supersonic, or hypersonic; thereby, allowing for forced establishing of the temperature of the first side providing for compensation of temperature changes within the first portion of the boundary layer; thereby, each of the elemental acoustic thermoelectric devices, providing for specific functionality of the elemental acoustic thermoelectric device, said specific functionality is specified as follows: when operating in the mode of sound launching: an electromagnetic wave is radiated in the ambient fluid due to the alternating electric current, wherein said electromagnetic wave is characterized by the alternation frequency; a difference between temperatures of the two opposite sides: first and second, of the thermoelectric element becomes alternating due to the Peltier effect; alternating changes in temperature of the first portion of the ambient fluid become created; and the alternating changes in temperature of the first portion of the ambient fluid, in turn, originate an acoustic wave propagating in the ambient fluid, said originated acoustic wave is characterized by a frequency, phase, amplitude, and net-efficiency of power consumption, all specified as follows: the acoustic wave frequency is equal to the alternation frequency, the acoustic wave phase is determined by a phase of the alternating changes in temperature of the first portion of the ambient fluid, the acoustic wave amplitude is determined by an amplitude of the alternating changes in temperature of the first portion of the ambient fluid, and the net-efficiency of power consumption is determined by a quality of the thermoelectric element, when operating in the mode of sound detection: the first portion of the ambient fluid is subjected to alternating changes in thermodynamic parameters: the static pressure, mass density, and absolute temperature; alternating changes in temperature of the first portion of the ambient fluid become created; the alternating temperature difference between the two opposite sides: first and second, generates the induced alternating electric current in the integrated circuit due to the Seebeck effect, wherein the induced alternating electric current is characterized by an alternation frequency equal to the frequency of the impacting acoustic wave; and the induced alternating electric current in the integrated circuit causes radiation of an electromagnetic wave propagating in the ambient fluid, wherein the electromagnetic wave is characterized by the alternation frequency. and when operating in the mode of boundary layer control: the first portion of the boundary layer, when characterized by sudden originated changes in thermodynamic parameters: the static pressure, mass density, and absolute temperature, wherein the sudden originated changes in the thermodynamic parameters determine originated acoustic waves; said acoustic waves are at least one of audible waves, ultrasound waves, shock waves, and Mach waves, is subjected to laminarization of motion by suppression of the sudden originated changes in the thermodynamic parameters and, thereby, by suppression of the acoustic waves; wherein the elemental acoustic thermoelectric devices are arranged at least one of: in alignment with a surface each near other, and by multilayer cascading one after another, thereby, providing for at least one of together-frontal in unison and multi-stage repeated action of at least one of: the Peltier effect to provide for: alternating changes in temperature of a multiplicity of portions of the ambient fluid; launching a multiplicity of said acoustic waves to form an acoustic beam composed of the acoustic waves; and radiating a multiplicity of said electromagnetic waves to form an electromagnetic signal composed of the electromagnetic waves, when the specific functionality of the acoustic thermoelectric device is as a functionality of an enhanced source of sound composed of motionless components and so allowing for generating an acoustic wave with reduced concomitant turbulence, thereby, providing for increasing net-efficiency of the enhanced source of sound, and the Seebeck effect to provide for a manifestation of detection of the impacting acoustic wave as follows: alternating heating and cooling of the first sides of the elemental acoustic thermoelectric devices, originating the induced alternating electric current in the elemental acoustic thermoelectric devices due to the Seebeck effect, alternating heating and cooling of the second sides of the elemental acoustic thermoelectric devices due to the Peltier effect; alternating heating and cooling of the second portion of the ambient fluid; launching a secondary acoustic wave from the second side; the secondary acoustic wave characterized by the alternation frequency and phase, wherein the phase at the second side differing from the phase of the impacting acoustic wave at the first side on 180°; and radiating an electromagnetic signal originated due to the induced alternating electric current in the elemental acoustic thermoelectric devices; when the specific functionality of the acoustic thermoelectric device is as a functionality of at least one of. an enhanced detector of sound composed of motionless integrated circuit components allowing for mutual compensation of said secondary acoustic wave and a portion of the impacting acoustic wave passed through the acoustic thermoelectric device and penetrated into the second portion of the ambient fluid, thereby, providing for increasing net-efficiency of the enhanced detector of sound, and a phase inverter composed of motionless integrated circuit components allowing for amplifying the induced alternating electric current such that said secondary acoustic wave is more powerful than a portion of the impacting acoustic wave passed through the acoustic thermoelectric device and penetrated into the second portion of the ambient fluid, thereby, providing dominance of said secondary acoustic wave over the portion of the impacting acoustic wave passed through the acoustic thermoelectric device and penetrated into the second portion of the ambient fluid; and wherein the controller-dispatcher being capable of controlling amplitudes, phase, delays, and frequencies of alternating electric currents generated in the elemental acoustic thermoelectric devices due to at least one of: functioning of the controllable generators, and the Seebeck effect; thereby allowing for the multiplicity of elemental acoustic thermoelectric devices to operate as a phased array.

2. A two-stage sound amplifier [5S.DEVICE] comprising a pair of the acoustic thermoelectric devices of claim 1: first and second, aggregated as a whole and operating in the sound detection mode; wherein: the second side of the first elemental acoustic thermoelectric device is adjacent to the first side of the second elemental acoustic thermoelectric device, and the first elemental acoustic thermoelectric device and the second elemental acoustic thermoelectric device are electrically separated, thereby, when: the two-stage sound amplifier is submerged in the ambient fluid such that the first side of the first acoustic thermoelectric device is thermally in contact with the first portion of the ambient fluid and the second side of the second acoustic thermoelectric device is thermally in contact with the second portion of the ambient fluid, and the first side of the first acoustic thermoelectric device is exposed to the impacting acoustic wave propagating in the ambient fluid wherein the impacting acoustic wave is characterized by a frequency being in a range of at least one of audible sound and ultrasound frequencies, manifestations of operation of the two-stage sound amplifier are as follows: the first portion of the ambient fluid is subjected to alternating changes in thermodynamic parameters: the static pressure, mass density, and absolute temperature; the alternating temperature difference between the two opposite sides: first and second, of the first elemental detector of sound induces an alternating electric current in the integrated circuit of the first elemental detector of sound due to the Seebeck effect, wherein the induced alternating electric current is characterized by the alternation frequency equal to the frequency of the impacting acoustic wave; the induced alternating electric current in the integrated circuit of the first elemental detector of sound results in anti-phase changes in temperature of both the second side of the first elemental detector of sound and the first side of the second elemental detector of sound due to the Peltier effect, the anti-phase changing in temperature of the first side of the second elemental detector of sound generates a secondary induced anti-phase alternating electric current in the integrated circuit of the second elemental detector of sound due to the Seebeck effect; the secondary induced anti-phase alternating electric current in the integrated circuit of the second elemental detector of sound results in changing in temperature of the second side of the second elemental detector of sound due to the Peltier effect, the changing in temperature of the second side of the second elemental detector of sound results in launching a secondary acoustic wave characterized by a phase at the second side of the second elemental detector of sound equal to the phase of the impacting acoustic wave at the first side of the first elemental detector of sound; and a superposition of substantially in phase: a portion of the impacting acoustic wave, which is passed through the pair of the elemental detectors of sound: first and second, aggregated as a whole, and the secondary acoustic wave, results in constructive interference manifested as a boosted acoustic wave.

3. A hearing aid comprising a phonendoscope supplied with the two-stage sound amplifier of claim 2.

4. An acoustic wireless charger [5T.SYSTEM] comprising: the acoustic thermoelectric device of claim 1 [5T.TX-ANTENNA] operating in the sound launching mode as the enhanced source of sound; the acoustic thermoelectric device of claim 1 [5T.RX-ANTENNA] operating in the sound launching mode as the enhanced detector of sound; a diode bridge [5T.B1B]; and a rechargeable battery [5T.B2B]; wherein: the first side [5T.71] of the enhanced detector of sound is exposed to an acoustic beam launched by the enhanced source of sound; the diode bridge is capable of transforming the induced alternating current into a direct current; and the rechargeable battery, when subjected to the direct current, is capable of becoming charged.

5. A nozzle [610, 650] having a corpus having a shaped tunnel within the corpus; the shaped tunnel having solid inner walls forming: an open inlet; an open outlet; and a varying cross-sectional area, varying along the shaped tunnel length having a distance parameter x such that a stationary geometry of the shaped tunnel is either converging, or divergent, or convergent-divergent; the solid inner walls are supplied with the acoustic thermoelectric device of claim 1 built-in into the solid walls; the acoustic thermoelectric device is further specified as follows: the multiplicity of the elemental acoustic thermoelectric devices aggregated as a whole in a surface matrix arrangement having two opposite sides: first and second, wherein the first side having a thermoconductive bus being thermally in contact with the solid inner walls and the second side having a thermoconductive bus being thermally in contact with a solid outer surface of the corpus contacting with ambient fluid; each of the thermoelectric elements is supplied with the integrated circuit representing the individual sensor-controller comprising the controllably manipulatable source of emf; and the controller-dispatcher capable of controlling each of the elemental acoustic thermoelectric devices as well as the acoustic thermoelectric device as a whole; the built-in acoustic thermoelectric device is capable of at least one of: consuming electric power to trigger the Peltier effect to provide a temperature difference between at least one of the solid inner wall of the shaped tunnel and the solid outer surface of the corpus contacting with the ambient fluid, and different points of the solid inner wall, and triggering the Seebeck effect to harvest electric power induced from a temperature difference between at least one of: the solid walls of the shaped tunnel and solid surfaces of the corpus contacting with ambient fluid, and different points of the solid walls; wherein, when the nozzle is exposed to fluid flow: entering the open inlet with a headway velocity u.sub.in, forming boundary layers adjacent to the solid inner walls, and outflow from the open outlet with a headway velocity u.sub.ou, the controller-dispatcher providing that the acoustic thermoelectric device causes forcedly distributed temperature along the solid inner walls, wherein the varying cross-sectional area of the shaped tunnel is characterized by a cross-sectional area profile function A(x) of x interrelated with functions u(x) and T(x) of x representing profiles of the fluid flow's headway velocity and absolute temperature, correspondingly, along the shaped tunnel length, wherein the thermoelectric device providing for a degree of freedom to interrelate the functions A(x), u(x), and T(x) by a condition of flow continuity expressed as: $A (x) = \frac{A_{*} \sqrt{(γ - 1) RT (x)}}{u (x)} {(\frac{2}{γ + 1} + \frac{{(u (x))}^{2}}{(γ + 1) RT (x)})}^{\frac{γ + 1}{2 (γ - 1)}}$ where A.sub.* is a constant, γ is an adiabatic compressibility parameter of the flowing fluid, and R is a specific gas constant characterizing the fluid flow, wherein the functions u(x) and T(x) both are gradually-smoothed monotonic, wherein: the gradually-smoothed monotonic function of the absolute temperature T(x) is determined by: an absolute temperature τ.sub.in of the fluid flow at the open inlet; temperature change δT.sub.0(x) interrelated with adiabatic compression-expansion occurred due to an adiabatic action of the Coanda-effect, in turn, determined by a curvature of the stationary geometry of the shaped tunnel, and forcedly established temperature contribution δT.sub.1(x) to the absolute temperature T(x) along the boundary layers subjected to controllable at least one of heating and cooling action of the thermoelectric device, such that T(x)=T.sub.in+δT.sub.0(x)+δT.sub.1(x), and the gradually-smoothed monotonic function of the fluid flow's headway velocity u(x) is determined by the headway velocity u.sub.in of the fluid flow at the open inlet, convective headway acceleration resulting in a velocity gradient along the shaped tunnel length as the fluid flow is subjected to the adiabatic Coanda-effect, and controllable headway acceleration occurred due to controllable heating and/or cooling action of the thermoelectric device; thereby, providing for conditions for a laminar motion of the fluid flow and beneficial features as follows: smoothing of the fluid flow's headway velocity profile function u(x), providing suppression of undesired turbulence; smoothing of the fluid flow's static pressure profile function P(x), providing suppression of undesired Mach waves and, thereby, suppression of vibrations of the nozzle corpus; smoothing of the fluid flow mass density profile function ρ(x), providing suppression of undesired disturbances of the fluid flow accompanied by shock waves; smoothing of the fluid flow absolute temperature profile function T(x), providing suppression of adjacent surface tensions; and smoothing of the fluid flow temperature-dependent M-velocity profile function M(x), providing a trade-off of suppressions of undesired all: the turbulence, vibrations, shock and Mach waves, and surface tensions.

6. A multi-stage nozzle composed of N nozzles of claim 5 consolidated as a whole; wherein the N nozzles, enumerated from 1 to N, are united together to join the N shaped tunnels associated with the N nozzles, correspondingly, such that each of the N shaped tunnels is a fragment of a resulting unbroken shaped tunnel formed thereby as a whole; an n-th fragment, where n is an integer between 1 and N: 1≤n≤N, has the varying cross-sectional area characterized by a cross-sectional area profile function A.sub.n(x) of x expressed as an individual condition of flow continuity: $A_{n} (x) = \frac{A_{* n} \sqrt{(γ - 1) {RT}_{n} (x)}}{u_{n} (x)} {(\frac{2}{γ + 1} + \frac{{(u_{n} (x))}^{2}}{(γ + 1) {RT}_{n} (x)})}^{\frac{γ + 1}{2 (γ - 1)}}$ where A.sub.*n is n-th constant, and the functions u.sub.n(x) and T.sub.n(x) are representing profiles of the fluid flow's headway velocity and absolute temperature, correspondingly, along the n-th fragment of the resulting unbroken shaped tunnel length; the resulting unbroken shaped tunnel as a whole is either converging, or divergent, or convergent-divergent, or two-stage convergent-divergent; or multi-stage convergent-divergent; wherein piecewise-monotonic profile functions u(x), P(x), ρ(x), T(x), and M(x), composed of associated gradually-smoothed monotonic profile functions concatenated together, all remain gradually-smoothed along the resulting unbroken shaped tunnel as a whole, thereby, the multi-stage nozzle is applicable to convey: in general, laminar flow to solve the problem of originated turbulence, and in particular, tiny portions of the fluid, associated with an acoustic wave incoming the open inlet and propagating within and along the resulting unbroken shaped tunnel, to solve the problem of sound power dissipation.

7. A sound amplifier comprising the mufti-stage nozzle of claim 6 and the acoustic thermoelectric device of claim 1, wherein the acoustic thermoelectric device is arranged nearby the open inlet and controlled by the controller-dispatcher to provide frequent changes in temperature of a nearby portion of the fluid to at least one of originate an acoustic wave and boost an incoming acoustic wave, to provide that when further the acoustic wave entering the open inlet of the shaped tunnel such that the fluid flow entering the open inlet with the headway velocity u.sub.in is a tiny portion of the fluid subjected to conveying motion inherently accompanying the acoustic wave entering the open inlet and propagating along the shaped tunnel; wherein the sound amplifier is either: a megaphone [7a.A], wherein: the resulting unbroken shaped tunnel is configured as a divergent funnel, an M-velocity of the conveying motion at the open inlet is higher than √{square root over ((γ−1)/γ)}, and the parameter x is a coordinate increasing along the divergent tunnel from the inlet to the outlet such that the profile function A(x) takes the value A.sub.* out of the divergent horn on the side of the open inlet; or a phonendoscope [7a.B], wherein the resulting unbroken shaped tunnel is two-stage convergent-divergent, further specified as comprising sequentially joint elements as follows: the open inlet characterized by an inlet cross-sectional area, indicated by A.sub.in, a convergent funnel characterized by a monotonically varying cross-sectional area; a first narrow throat characterized by a local minimal cross-sectional area, indicated by A.sub.th1; a widened cavity characterized by a local maximal cross-sectional area, indicated by A.sub.ca; a second narrow throat characterized by a local minimal cross-sectional area, indicated by A.sub.th2; a divergent funnel characterized by a monotonically varying cross-sectional area; and the open outlet characterized by an outlet cross-sectional area, indicated by A.sub.ou; wherein conditions: A.sub.in/A.sub.th1≥√{square root over (γ/(γ−1))}, A.sub.ca/A.sub.th1>1, A.sub.ca/A.sub.th2≥√{square root over (γ/(γ−1))}, A.sub.th2/A.sub.th1≤1, and A.sub.ou/A.sub.th2≥√{square root over (γ(γ−1))}, are satisfied to provide that the phonendoscope becomes capable of amplifying a loudness of an incoming sound yet to become subjected to an action of the phonendoscope; or a hearing aid [7a.C] embodied as the phonendoscope, wherein said corpus has an outer geometrical configuration ergonomically adapted to a human's ear canal, such that the open outlet is faced to an eardrum within the human's ear canal.

8. An airfoil capsule [720, 740] comprising an airfoil outer overall shape and at least one of the nozzle of claim 5 and the multi-stage nozzle of claim 6.

9. An airfoil wing [8.00, 800] comprising at least one of the nozzle of claim 5 and the multi-stage nozzle of claim 6 [8.31, 8.32], wherein the shaped tunnel further having an imaginary wall formed by streamlines of the fluid flow; wherein the corpus of the multi-stage nozzle is further specified as having an airfoil geometrical configuration recognizable by a sectional elongated profile, comprising two opposite curved sides: an upper side and a lower side, and two opposite butt-ends: forward being rounded and rearward being sharp, such that when the airfoil wing is exposed to an oncoming portion of the fluid flow, the oncoming portion flowing around the airfoil wing becomes divided into two sub-portions: an upper-side sub-portion of the oncoming portion of the fluid flow forming an upper-side boundary layer and a lower-side sub-portion of the oncoming portion of the fluid flow forming a lower-side boundary layer; wherein the upper side comprising: a forward part meeting the upper-side boundary layer; an upper-side convexity, where the upper-side boundary layer, when sliding upon the upper-side convexity, has an imaginary narrowed cross-section; a rearward part, attracting and, thereby, redirecting mass-center of the sliding upper-side boundary layer backward-downward due to the Coanda-effect, thereby causing an imaginary widened cross-section of the sliding upper-side boundary layer nearby the rearward part; and the built-in acoustic thermoelectric device along the upper side for distributed heating or cooling the upper-side boundary layer; and wherein the lower side is curved to form a lower-side convexity; said lower-side meeting the lower-side boundary layer, wherein: a sagittal axis [820.0] is defined as an axis codirected with a motion of the oncoming portion of the fluid flow yet to be subjected to an action of the airfoil wing; an attack angle is defined as an angle between a sagittal axis and a direction of motion tendency of said lower-side boundary layer when the lower-side boundary layer outflowing nearby and stalling from the sharp rearward butt-end of the airfoil wing; and a zero attack angle is specified as said attack angle equal to zero; wherein the airfoil geometrical configuration is further specified such that, when the airfoil wing is exposed to the oncoming portion of the fluid flow at the zero attack angle: the sectional elongated profile of the airfoil wing is either mirror-symmetrical [8.00] or asymmetrical [800] relative to a sagittal axis; and each of the two boundary layers: upper-side and lower-side, representing said shaped tunnel: upper-side or lower-side, correspondingly, further having an imaginary wall formed by streamlines bordering associated said boundary layer: upper-side or lower-side, correspondingly; thereby, providing for: improved laminarity of the portion of the fluid flowing around the airfoil wing; that, when stalling from the sharp rearward butt-end of the airfoil wing, the upper-side and lower-side boundary layers, both have the same headway velocity u.sub.ou, and the same thermodynamic parameters: the static pressure, mass density, and absolute temperature, such that the two boundary layers: upper-side and lower-side, when joining together to move as a whole downstream behind the airfoil wing, form a uniform resulting outflowing portion of the fluid flow remaining laminar; improving wing properties manifested as: decreased drag, increased lift-force due to improved laminarity of the fluid flow, and, when the upper side of the airfoil wing is colder than the lower side of the airfoil wing, further increased lift-force due to imitating an effect of taking-off of a bird; overcoming a problem of efficient use of another airfoil wing arranged downstream behind the airfoil wing; and a benefit of in-line cascading a next said airfoil wing after a previous said airfoil wing resulting in increased cumulative lift-force.

10. A tandem of two airfoil wings of claim 9 consolidated as a whole [880.B]; the tandem is exposed to an oncoming portion of fluid flow; the two airfoil wings: first and second, are arranged to meet the oncoming portion [851.B] of the fluid flow, divide the oncoming portion of the fluid flow into two sub-portions: an upper-side sub-portion of the oncoming portion of the fluid flow forming an upper-side boundary layer [852.B1, 853.B1, 854.B1, 852.B3, 853.B3, 854.B3] and a lower-side sub-portion of the oncoming portion of the fluid flow forming a lower-side boundary layer [852.B2, 853.B2, 854.B2, 852.B4, 853.B4, 854.B4], and act on at least one of the boundary layers: upper-side and lower-side, sequentially in two stages: first and second, namely: at the first stage, the first airfoil wing, meeting the oncoming portion of the fluid flow yet to be subjected to the Coanda-effect and acting on the oncoming portion of the fluid flow by the Coanda-effect, and at the second stage, the second airfoil wing, meeting the oncoming portion of the fluid flow already subjected to the action by the first airfoil wing at the first stage; wherein: a specific M-velocity is defined as √{square root over ((γ−1)/γ)}; a first convexity is defined as at least one of the upper-side and lower-side convexity [869.B1 or 869.B2] of the first airfoil wing; and a second convexity is defined as at least one of the upper-side and lower-side convexity [869.B3 or 869.B4] of the second airfoil wing; such that at least one of the two boundary layers: upper-side and lower-side, each of which originated adjacent to the upper or lower side of the tandem of two airfoil wings, correspondingly, is composed of two parts: first, flowing nearby the first convexity, and second, flowing nearby the second convexity; each of the two boundary layers: upper-side or lower-side, is subjected to at least one of: the Venturi effect, when an M-velocity of the upper-side or lower-side boundary layer, correspondingly, remains lower than the specific M-velocity; the de Laval effect of flow acceleration nearby the first convexity and to de Laval effect of flow retarding nearby the second convexity, when an M-velocity of the oncoming portion of fluid flow [851.B] is lower than the specific M-velocity and sufficiently high to reach the specific M-velocity nearby the first convexity; or the de Laval effect of flow retarding nearby the first convexity and to de Laval effect of flow acceleration nearby the second convexity, when an M-velocity of the oncoming portion of fluid flow [851.B] is higher than the specific M-velocity; such that the varying cross-sectional areas of the parts of the boundary layer: first, flowing nearby the first convexity, and second, flowing nearby the second convexity, are characterized by cross-sectional area profile functions A.sub.1(x.sub.1) and A.sub.2(x.sub.2) of distance parameters x.sub.1 or x.sub.2, correspondingly; each of the cross-sectional area profile functions A.sub.1(x.sub.1) and A.sub.2(x.sub.2) is given by the individual condition of flow continuity wherein the distance parameter x is x.sub.1 or x.sub.2 associated with the parts of the boundary layer: first, flowing nearby the first convexity, and second, flowing nearby the second convexity, correspondingly, thereby, providing for that the tandem of two airfoil wings consolidated as a whole has a positive lift-force for low M-velocities, lower than the specific M-velocity, and for high M-velocities, higher than the specific M-velocity.

11. A double-humped wing [870] comprising the tandem of two airfoil wings of claim 10 wherein the two airfoil wings are merged as a whole to form an unbroken double-humped corpus such that to act on the upper-side boundary layer sequentially in two stages: first and second, thereby, providing for that the double-humped airfoil wing has a positive lift-force for low M-velocities, lower than the specific M-velocity, and for high M-velocities, higher than the specific M-velocity.

12. A jet-rotor [9.7] comprising an axle [9.73] oriented along a sagittal axis and supplied with a set of blades, wherein the set of blades is a set of at least one of: the airfoil wings of claim 9; the tandems of two airfoil wings consolidated as a whole of claim 10; and the double-humped wings of claim 11; the blades are oriented to: be exposed to the oncoming portion of the fluid flow at the zero attack angle and thereby subjected to an action of lift-forces originated due to the Coanda-effect dominantly, wherein the Coanda-effect is accompanied by at least one of: the Venturi effect; and the de Laval jet-effect; and vector the originated lift-forces in a frontal plane perpendicular to the sagittal axis to rotate the axle around the sagittal axis in unison, thereby, providing for: improved laminarity of the oncoming portion of the fluid flow when flowing around the jet-rotor; suppression of turbulence of the oncoming portion of the fluid flow when moving downstream behind the jet-rotor, and increased lift-forces acting in unison and in the same direction of rotation and so rotating the axle, when the de Laval jet-effect is triggered.

13. A jet-turbine [9.7] comprising: an engine, having a stator and rotatable shaft, and the jet-rotor of claim 12; wherein the axle [9.73] is attached to the rotatable shaft to provide for the rotatable shaft to be rotated in unison with the axle rotation around the sagittal axis, thereby, providing for: increased efficiency of the jet-turbine in a wide range of wind velocities; overcoming the problem to efficient use a wind turbine adjacently arranged downstream behind another wind turbine, and a benefit of in-line cascading a next said jet-turbine immediately after a previous said jet-turbine resulting in increased cumulative efficiency of producing electricity.

14. A tuple of the jet-turbines of claim 13, wherein the jet-turbines are arranged in-line along a common sagittal axis one downstream behind another.

15. An enhanced jet-propeller [9K.0] comprising: a motor, having a stator and rotatable shaft, and a jet-rotor [9K.0] having an axle supplied with a tuple of sets of blades [9K.1, 9L.01, 9L.02] in-line arranged sequentially one after another along a sagittal axis, wherein: the axle is attached to the rotatable shaft to provide for the rotatable shaft to be rotated in unison with the axle rotation around the sagittal axis; and each of the sets [9K.1, 9L.01, 9L.02] of blades is composed of at least one of: the airfoil wings of claim 9, the tandem of two airfoil wings consolidated as a whole of claim 10, and the double-humped wings of claim 11; wherein: a pitch, as a measure of a blade orientation, is defined as an angle between the sagittal axis and an angle of view defined for the blade of the jet-rotor being stationary; each of the sets of blades comprises blades assembled with an individual pitch, adapted to a rate of a forced rotation of the rotatable shaft and axle, such that each of the blades runs over portions of the fluid flow [9K.6, 9L.6, 9M.6] at the zero attack angle and, thereby, is: subjected to an action of lift-force [9K.3] originated due to the Coanda-effect dominantly, wherein the Coanda-effect is accompanied by at least one of the Venturi effect; and the de Laval jet-effect; and vectored to have a dominant component of headway motion collinear to the sagittal axis; thereby, due to the Coanda-effect dominantly, each of the blades acts on the portions of the fluid flow by a pushing force vectored against the component of lift-force according to Newton's third law and so to accelerate the portions of the fluid flow in conformance with the vectored pushing force thereby resulting in a dominantly-laminarly headway-forwarding fluid flow directed along the sagittal axis.

16. A tuple of the enhanced jet-propellers of claim 15, wherein the enhanced jet-propellers [9L.0, 9M.01, 9M.02] are arranged in-line along the sagittal axis [9M.7] one downstream behind another.

17. A heat-transformer [710.H] comprising: the nozzle of claim 5; and a reservoir [712.B] having walls supplied with: pipes [715.B], each of which having a through-hole tunnel allowing for an ambient fluid portion to enter the reservoir and become an inner fluid portion; the through-hole tunnel having a sectional profile being either symmetric relative to a cross-sectional plane or asymmetric with a property of a valvular conduit (Tesla valve); and a multiplicity of thermoelectric devices [714.B] capable of heating the inner fluid portion to trigger a motion of the heated inner fluid portion [711.B] toward the shaped tunnel of the nozzle [710.B].

18. A heat-turbine [9n.H] comprising: the nozzle of claim 5 wherein the shaped tunnel [9n.1] is oriented along a vertical sagittal axis [9n.51]; a heater capable of heating a portion of the ambient fluid to trigger the Archimedes' upward-vectored force lifting the heated fluid portion and thereby to create an upward-moving dominantly-laminarly headway-forwarding fluid flow; and the jet-turbine [9.n3] of claim 9 capable of transforming the kinetic power of the jet-rotor rotation into electric power; wherein: said heater is capable to increase an absolute temperature of the portion of the ambient fluid entering the shaped tunnel up to a value T.sub.in being higher than the absolute temperature T.sub.a of the ambient fluid outside the nozzle such that ratio T.sub.in/T.sub.a is at least 1.2 to provide a condition that when the upward-moving dominantly-laminarly headway-forwarding fluid flow moves within the converging funnel and becomes subjected to the Venturi effect, the upward-moving dominantly-laminarly headway-forwarding fluid flow reaches the specific M-velocity within the narrow throat and so triggering the de Laval jet-effect; and the jet-rotor of the jet-turbine is arranged either: within the shaped tunnel near or downstream behind the narrow throat, where the M-velocity is determined by the specific M-velocity, or immediately beyond the open outlet, where the M-velocity is determined by a cross-sectional area of the open outlet according to the condition of flow continuity; the jet-rotor of the jet-turbine is arranged to be exposed to said upward-moving dominantly-laminarly headway-forwarding fluid flow moving through and outflowing from the shaped tunnel such that all the blades of the jet-rotor are oriented to meet portions of said dominantly-laminarly headway-forwarding fluid flow at the zero attack angle; wherein an overall shape of the blades is adapted to the M-velocity dependent on the x coordinate along the sagittal axis to satisfy conditions of said upward-moving dominantly-laminarly headway-forwarding fluid flow; thereby, providing for: creation of the upward-moving dominantly-laminarly headway-forwarding fluid flow due to triggering the Archimedes' upward-vectored force lifting the heated portion of the ambient fluid; an acceleration of the upward-moving dominantly-laminarly headway-forwarding fluid flow within the shaped tunnel due to the Venturi effect triggering the de Laval jet-effect for further acceleration of the upward-moving dominantly-laminarly headway-forwarding fluid flow within the shaped tunnel; powering the jet-turbine exposed to the accelerated upward-moving dominantly-laminarly headway-forwarding fluid flow; overcoming a problem of efficient producing electricity from the heated portion of the ambient fluid; and a benefit of triggering the Archimedes' upward-vectored force lifting the heated portion of the ambient fluid and triggering the de Laval jet-effect for producing electricity.

19. A jet-transformer [9n.J] comprising: the nozzle of claim 5; the enhanced jet-propeller of claim 15, the enhanced jet-propeller capable of creating said dominantly-laminarly headway-forwarding fluid flow directed along the sagittal axis; and the jet-turbine of claim 13 capable of transforming the kinetic power of the jet-rotor rotation into electric power; wherein: the enhanced jet-propeller providing for that the dominantly-laminarly headway-forwarding fluid flow, when entering the open inlet having the distance parameter indicated by x.sub.in, has an M-velocity equal to M(x.sub.in) estimated according to the condition of flow continuity such that the dominantly-laminarly headway-forwarding fluid flow, when moving along the converging funnel and becoming subjected to the Venturi effect, reaches the specific M-velocity within the narrow throat and so triggering the de Laval jet-effect wherein distribution of M-velocities along the sagittal axis is determined by the value M(x.sub.in) of the M-velocity at the open inlet having the cross-sectional area A(x.sub.in); and the jet-rotor of the jet-turbine is arranged either: within the shaped tunnel near or downstream behind the narrow throat, where the M-velocity is determined by the specific M-velocity, or immediately beyond the open outlet, where the M-velocity is determined by a cross-sectional area of the open outlet according to the condition of flow continuity; the jet-rotor of the jet-turbine is arranged to be exposed to said dominantly-laminarly headway-forwarding fluid flow moving through and outflowing from the shaped tunnel such that all the blades of the jet-rotor are oriented to meet portions of said dominantly-laminarly headway-forwarding fluid flow at the zero attack angle; wherein an overall shape of the blades is adapted to the M-velocity dependent on the x coordinate along the sagittal axis to satisfy conditions of said dominantly-laminarly headway-forwarding fluid flow; thereby, providing for: creation of the upward-moving dominantly-laminarly headway-forwarding fluid flow due to triggering the Coanda-effect using the jet-ventilator; an acceleration of the upward-moving dominantly-laminarly headway-forwarding fluid flow within the shaped tunnel due to the Venturi effect; triggering the de Laval jet-effect for further acceleration of the upward-moving dominantly-laminarly headway-forwarding fluid flow within the shaped tunnel; powering the jet-turbine exposed to the accelerated upward-moving dominantly-laminarly headway-forwarding fluid flow; and overcoming a problem of a benefiting use of the de Laval jet-effect for producing electricity.

20. A levitating apparatus [9o.0] comprising: the enhanced jet-propeller [9o.1] of claim 15, the enhanced jet-propeller capable of creating said dominantly-laminarly headway-forwarding fluid flow; and a capsule [9o.2] having a shell composed of two parts: upper and lower; wherein said shell has a dominantly-airfoil overall shape and is supplied with built-in thermoelectric elements capable of supporting gradually distributed temperature, distributed along the shell; wherein the jet-rotor is located above the capsule such that to be capable of blowing the shell of the capsule from above by the dominantly-laminarly headway-forwarding fluid flow; thereby, providing for that, when the upper sides of the jet-rotor blades are colder than the lower sides of the enhanced jet-rotor wings, an effect of taking-off of the levitating apparatus due to an imitated effect of taking-off of a bird is originated; and when the upper part of the shell is colder than the lower part of the shell, an effect of taking-off of the levitating apparatus due to an imitated effect of taking-off of an insect is originated.

21. The levitating apparatus of claim 20 further comprising at least one of the airfoil capsule of claim 8, the heat-transformer of claim 17, and the jet-transformer of claim 19.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0310] 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, referring to the accompanying drawings, in the drawings:

[0311] Of Prior Arts:

[0312] FIG. 1b is a schematic drawing of the convergent-divergent Venturi tube;

[0313] FIG. 1c is a schematic view of the convergent-divergent de Laval nozzle;

[0314] FIG. 1d is a schematic illustration graphics of gas velocity, static pressure, and temperature distributions within the de Laval convergent-divergent jet-nozzle;

[0315] FIG. 1f is a schematic drawing of a body blown by an airflow portion;

[0316] FIG. 1g is a schematic drawing of a classic prior art asymmetrical and mirror-symmetrical profiles of an airplane wing;

[0317] FIG. 1i is a schematic illustration of points of sail;

[0318] FIG. 1j is an illustration of a honeybee as an exemplary insect capable of flying;

[0319] FIG. 1k is a schematic illustration of a wind turbine, built-in into a cylinder;

[0320] FIG. 1n, composed of three parts: Case (A), Case (B), and Case (C), comprises prior art schematic drawings of megaphones and a gramophone, each supplied by a horn;

[0321] FIG. 1L is a schematic drawing of a human ear profile in a sagittal plane;

[0322] FIG. 1o is a schematic drawing of a thermocouple;

[0323] FIG. 1p is a schematic drawing of a thermoelectric element;

[0324] FIG. 1q is a schematic drawing of a thermoelectric multi-module device;

[0325] FIG. 1r is an exemplary planar arrangement of thermoelectric elements;

[0326] FIG. 1t is a schematic drawing of a thermoelectric multi-module device; and

[0327] Of Embodiments, Constructed According to the Principles of the Present Invention:

[0328] FIG. 5p is a schematic illustration of an elemental source and detector of sound;

[0329] FIG. 5q is a schematic illustration of a matrix of elemental sources and detectors of sound;

[0330] FIG. 5r is a schematic illustration of a multi-module thermoelectric device;

[0331] FIG. 5s is a schematic illustration of a two-stage sound amplifier;

[0332] FIG. 5t is a schematic illustration of a communication system;

[0333] FIG. 6a is a schematic illustration of an optimized convergent-divergent jet-nozzle;

[0334] FIG. 6b is a schematic illustration of an optimized inverse convergent-divergent nozzle;

[0335] FIG. 6c is a schematic illustration of a two-stage convergent-divergent jet-nozzle;

[0336] FIG. 7 shows comparative graphs of the dependencies of the nozzle extension ratio vs. the airflow M-velocity, calculated by the classical and suggested models;

[0337] FIG. 7a, composed of three parts: case (A), case (B), and case (C), comprises schematic illustrations of sound boosters where: case (A) is a horn for a gramophone, case (B) is a phonendoscope, and case (C) is a hearing aid;

[0338] FIG. 7b is a schematic illustration of a compressor supplied by an optimized convergent-divergent jet-nozzle;

[0339] FIG. 7c is a schematic sectional view of a flying capsule;

[0340] FIG. 7d is a schematic sectional view of a flying capsule;

[0341] FIG. 8 is a schematic illustration of a symmetrical wing supplied with a TE device;

[0342] FIG. 8a is a schematic illustration of an actually-airfoil wing blown by the wind;

[0343] FIG. 8b is a schematic illustration of a flying airfoil body;

[0344] FIG. 8c is a schematic illustration of flying airfoil bodies;

[0345] FIG. 8d is a schematic illustration of two-stage airfoil wings;

[0346] FIG. 9a is a schematic illustration of a sequential cascade of airfoil bodies;

[0347] FIG. 9b is a schematic illustration of an in-line cascade of rings having airfoil walls;

[0348] FIG. 9c is a schematic illustration of two Archimedean screws having airfoil walls;

[0349] FIG. 9g is a schematic drawing of an improved wind-turbine;

[0350] FIG. 9h is a schematic side and front views of an improved wind-turbine;

[0351] FIG. 9j is a schematic illustration of a jet-ventilator;

[0352] FIG. 9k is a schematic illustration of a jet-propeller;

[0353] FIG. 9L is a schematic illustration of a multi-module jet-ventilator;

[0354] FIG. 9m is a schematic illustration of cascaded multi-module jet-propellers; and

[0355] FIG. 9n is a schematic illustration of a jet-transformer.

[0356] FIG. 9o is a schematic illustration of a levitating apparatus.

[0357] 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

[0358] The principles and operation of a method and an apparatus according to the present invention may be better understood referring 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.

Preface

[0359] The jet-effect occurring in moving fluid can be manifested as: [0360] the Venturi effect and the de Laval jet-effect resulting in either: [0361] convective self-acceleration accompanied by self-cooling, or [0362] self-retarding accompanying by self-warming, [0363] when a portion of the headway moving fluid is subjected to a reshaping; [0364] the Coanda-effect resulting in both: [0365] lift-force acting on a profiled wing, and [0366] thrust-force acting on a sail oriented as so-called “B-Point of Sail”; [0367] when a convexly-curved surface is tangentially blown by a headwind; and [0368] the waving jet-effect resulting in both: [0369] acoustic wave (audible sound or ultrasound) origination, and [0370] conveying of a tiny portion of fluid transmitting wave energy away along the direction of the acoustic wave propagation; [0371] when a portion of the fluid is subjected to oscillating change in static pressure;
wherein these are manifestations of the jet-effect defined as an effect of transformation of the heat power into the kinetic power of fluid motion as a whole and, vice-versa, an effect of transformation of the kinetic power of fluid motion as a whole into the heat power. Further, the DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS is divided between two paragraphs: “Conceptual Idea” and “Embodiments”, each having sub-paragraphs.

Conceptual Idea

Prerequisites:

[0372] On the one hand, an inertialess controller is required; namely, in general, as a fluid flow acceleration is accompanied by varying thermodynamic parameters of portions of the fluid wherein the interrelation between the varying thermodynamic parameters is inertialess, control of the fluid flow should be if not inertialess then at least almost inertialess to provide the desired control of the thermodynamic parameters efficiently; and, in particular, [0373] as the Coanda-effect, that manifested by pulling-in the fluid portions forming a boundary layer and causing a lift-force, is accompanied by changes in thermodynamic parameters of the fluid portions wherein the interrelation between the changes is inertialess, a controller of the changes should be if not inertialess then at least almost inertialess to provide the desired boundary layer and lift-force; [0374] as the Venturi effect and the de Laval effect, both accompanied by the fluid portions' reshaping and inertialessly interrelated changes in thermodynamic parameters, again, a controller of the changes should be if not inertialess then at least almost inertialess to provide the desired thermodynamic parameters meeting the conditions of flow laminarity; [0375] as the upward-vectored lift-force is the property of the ambient-adjacent boundary layer, likewise, a controller of the changes in the thermodynamic properties of the ambient-adjacent boundary layer should be if not inertialess then at least almost inertialess to provide the desired property of the ambient-adjacent boundary layer; and [0376] as a sound propagating in the fluid is accompanied by oscillating changes: δP, δρ, and δT, of thermodynamic parameters: the static pressure, mass density, and absolute temperature, correspondingly, of the fluid portions wherein the interrelation between the changes is inertialess, alike, a controller of a source of the sound should be if not inertialess then at least almost inertialess to provide the desired frequency of oscillating changes; and [0377] On the other hand, an almost inertialess thermoelectric device having no moving parts can be used namely, considering a thermoelectric (TE) device based on the Peltier effect, the almost inertialess interrelation between the current density J and the temperature difference ΔT, at least when removing the accumulated heat away is extra-fast and/or when the desired temperature difference ΔT is extremely small, makes using the TE device (optionally made using Nano-technologies from a thermoelectric material of high quality) promising, in general, to control the changes of the thermodynamic parameters of the moving fluid, and, in particular, to: [0378] create and control the lift-force; wherein, taking into attention that the TE device does not have moving parts, the using the TE device allows to create and control the lift-force without the creation of undesired turbulence, thereby, to create and control the lift-force much more efficiently than using wings supplied with moving flaps; [0379] create and control laminarity of a flow within a convergent-divergent nozzle: either a Venturi pipe or a de Laval tube; wherein, taking into attention that the TE device does not have moving parts, the using the TE device allows smoothing the distributed static pressure to suppress so-called Mach waves and thereby to control the laminarity; and [0380] create, detect, and suppress the acoustic waves; wherein, as the TE device does not have moving parts, the using the TE device allows creating the acoustic waves without the creation of undesired turbulence, thereby, to launch and detect the acoustic waves (sound or ultrasound) much more efficiently than using classical speakers and microphones, correspondingly, which are supplied with a moving membrane.

Essence of Concept

[0381] Thus, the conceptual idea of the present invention is in the use of a thermoelectric device to: [0382] control gradients of thermodynamic parameters of flow along a convergent-divergent nozzle: either a Venturi pipe or a de Laval tube; [0383] create a pressure difference between the upper and lower sides of an airfoil body (for instance, a wing) to originate and control lift-force; [0384] create a pressure difference between anterior and tail parts of an airfoil body to originate and control thrust; [0385] create the oscillating changes: δP, δρ, and δT, of thermodynamic parameters: the static pressure, mass density, and absolute temperature, correspondingly, of a portion of the fluid, to pull-in and push-off the fluid portion, and, thereby, to create acoustic waves; and, vice-versa, [0386] detect and/or suppress the oscillating changes: δP, δρ, and δT, of thermodynamic parameters: the static pressure, mass density, and absolute temperature, correspondingly, of a portion of the fluid, and thereby to detect and/or suppress the acoustic waves.
The conceptual idea, being one of the primary features of the present invention, lies in the basis of the disclosed method and aerodynamic apparatuses (fluid pushers-off and fluid motion-sensors) for the creation and controlling of lift-force and thrust and for the creation and detection of sound.

Embodiments

Elemental TE Device as Source of Sound

[0387] FIG. 5p is a schematic illustration of an elemental acoustic thermoelectric device 5P.0, capable of functioning in two controllable modes: “A”, to originate temperature difference between two buses 5P.7A and 5P.5A using the Peltier effect and, “B”, vice versa, to detect the temperature difference between two buses 5P.7B and 5P.5B using the Seebeck effect.

[0388] The mode “A” is a case of forced controlling the temperature and thereby the static pressure of a portion of the ambient fluid, wherein the changes in temperature and static pressure are mutually-interrelated according to the equations Eq. (1.1b) and Eq. (1.3c). The mode of forced-varying temperature assumes that the varying of the temperature and thereby the static pressure of the portion of the ambient fluid is periodically alternating, i.e. increasing and decreasing the static pressure that, in turn, indicates to generating an elastic (acoustic) wave propagating in the ambient fluid. The mode “A” is concretized as Case (A) SOUND LAUNCHING MODE. The feature is that the acoustic wave permanently transmits the wave energy away from the source in the direction of the Umov-vector collinear with the direction of the acoustic wave propagation. Thus, the elemental acoustic thermoelectric device 5P.0 operating in the mode “A” becomes interpreted as an aerodynamic apparatus—a fluid pusher-off, which is pulling-in and pushing-off a portion of the fluid and, thereby, is capable of triggering the conveying motion of a tiny portion of the ambient fluid (the conveying motion associated with the acoustic wave propagation), wherein the necessity of a powerful ventilator is excluded.

[0389] The mode “B” is a case of detecting the periodically alternating temperature changes of a portion of the ambient fluid. Again, the varying static pressure of the portion of the ambient fluid is interpreted as an indication of the presence of an elastic wave. So, the elemental acoustic thermoelectric device 5P.0 operating in the mode “B” becomes interpreted as an aerodynamic apparatus—a fluid motion-sensor, and the mode “B” is concretized as Case (B) SOUND DETECTION MODE.

[0390] Thus, the elemental acoustic thermoelectric device 5P.0, called an ELEMENTAL SOURCE AND DETECTOR OF SOUND, constructed according to the principles of the present invention, is an aerodynamic apparatus: a fluid pusher-off and/or a fluid motion-sensor, capable of operation in the two modes: Case (A) SOUND LAUNCHING MODE and Case (B) SOUND DETECTION MODE, as either an ELEMENTAL SOURCE OF SOUND 5P.0A or an ELEMENTAL DETECTOR OF SOUND 5P.0B, correspondingly.

[0391] From the point of view of construction, the two cases: Case (A) SOUND LAUNCHING MODE and Case (B) SOUND DETECTION MODE, differ as follows: [0392] In the Case (A) SOUND LAUNCHING MODE, an ELEMENTAL SOURCE OF SOUND 5P.0A comprises a TE element 5P.A supplied with an individual controller 5P.8A connected between the connection points 5P.61A and 5P.62A and comprising an integrated circuit (IC) 5P.81A and a manipulatable source of emf 5P.82A, wherein two opposite sides of the TE element 5P.A comprise, on the one side, an ACTIVE COOLING AND HEATING BUS 5P.7A and, on the other side, a HEAT AND COLDNESS REJECTION BUS 5P.5A, both merged in the ambient fluid and wherein the manipulations in the polarity of the source of emf 5P.82A are periodically oscillating such that the originated oscillating temperature differences between the two opposite sides interrelated with whereby originated oscillating pressure differences are regarded as indicators of the presence of an acoustic wave propagating and transmitting the heat energy away from the ELEMENTAL SOURCE OF SOUND 5P.0A as the wave energy, and hence preventing the heat accumulation near the ELEMENTAL SOURCE OF SOUND 5P.A; [0393] and [0394] In the Case (B) SOUND DETECTION MODE, an ELEMENTAL DETECTOR OF SOUND 5P.0B comprises a TE element 5P.B supplied with an individual controller IC DETECTOR 5P.8B comprising an integrated circuit (IC) and a detector of an induced varying electric current [for instance, alternating current (AC)] originated by the TE element 5P.B when a HEAT AND COLDNESS SOURCE BUS 5P.7B is exposed to ambient fluid and subjected to impacting acoustic wave characterized by varying heating and cooling of a tiny portion of the ambient fluid adjacent the HEAT AND COLDNESS SOURCE BUS 5P.7B, wherein the varying heating and cooling are manifested as periodically oscillating pressure and temperature, wherein, as the acoustic wave prevents the heat accumulation near the ELEMENTAL DETECTOR OF SOUND 5P.0B, one does not need in forcible thermostating the ELEMENTAL DETECTOR OF SOUND 5P.B;

[0395] The inventor points out, again, that, the thermoelectric elements: 5P.A and 5P.B, as well as the thermoelectric elements 1.0 (1.0A and 1.0B) described hereinabove in THE BACKGROUND OF THE INVENTION referring to FIG. 1p, are characterized by the time-invariant interrelation between the current density j and the temperature difference ΔT. On the other hand, the time-invariance allows implementing the elemental acoustic thermoelectric devices 5P.0: an ELEMENTAL SOURCE OF SOUND 5P.0A and ELEMENTAL DETECTOR OF SOUND 5P.0B, such that: [0396] in the Case (A) SOUND LAUNCHING MODE, the ELEMENTAL SOURCE OF SOUND 5P.0A functioning in the SOUND LAUNCHING MODE differs from TE element 1.0A (FIG. 1p Case (A) REFRIGERATION MODE) functioning in the REFRIGERATION MODE and normally supplied with the ventilator 1.9A by that the source 1.6A of DC emf and the ventilator 1.9A, altogether are now replaced by an individual controller 5P.8A having the integrated circuit IC 5P.81A and the manipulatable source of emf 5P.82A controlled by the integrated circuit IC 5P.81A such that the manipulatable source of emf 5P.82A is capable of generating an alternating emf of a frequency f in the range of frequencies of the audible sound and ultrasound, i.e. from 20 Hz and lower to 20 kHz and higher; wherein, optionally, the individual controller 5P.8A can be implemented as a block 5P.80A of an electric scheme supplied by a transformer as 5P.86A of the alternating current and voltage that (the transformer 5P.86A), [0397] on the one hand, is connected to the metallic electrical contact pads 5P.41A and 5P.42A of an n-type (negative thermopower and electron carriers) semiconductor material 5P.1A and of a p-type (positive thermopower and hole carriers) semiconductor material 5P.2A, correspondingly, and [0398] on the other hand, is connected to the generator of alternating current and voltage 5P.820A, which is manipulatable by an individual integrated circuit IC 5P.810.A, [0399] to separate the AC generated by the generator 5P.820A and the AC induced in the circuit of the TE element 5P.A; wherein, referring to exemplary TE modules, made using Nano-technologies, characterized by the estimated local temperature rate is 1.25 C/sec the estimated local temperature rate is 1.25 C/sec as described hereinabove in THE BACKGROUND OF THE INVENTION referring to FIG. 1p Case (A) TIME CHARACTERISTIC and citing D4, the estimations of reachable SPL for audible sound are as follows: [0400] when 20 Hz sound is required, half of the time-period allowing for the temperature oscillation is 0.5×τ.sub.20 Hz=0.025 sec and the reachable amplitude of the temperature difference is approximately 0.03K that corresponds to SPL=SDL=STL level of 155 dB; [0401] when 20 kHz sound is required, half of the time-period allowing for the temperature oscillation is 0.5×τ.sub.20 kHz=2.5×10.sup.−5 sec and the reachable amplitude of the temperature difference is, approximately, 3×10.sup.−5 K that corresponds to SPL=SDL=STL level of 95 dB; [0402] The investor points out that the estimation is the worst-case estimation made with a spare reserve because the generated sound transmits the heat and coolness away with the velocity of sound in the ambient fluid, i.e., on the one hand, one does not need to use a ventilator for the heat removing (note, the gusty-choppy operating ventilator would not allow to generate so precise temperature differences), and, on the other hand, the not accumulated heat provides for desired inertialess of the thermoelectric element functioning. In other words, the SPL, much higher than the worst-case estimated 95 dB, is reachable. Thus, in any case, the reachable SPL is much higher than the usually used SPL between 0 to 80 dB, and so the ELEMENTAL SOURCE OF SOUND 5P.0A is capable to launch acoustic waves as audible sound 5P.91A and 5P.92A, launched from the ACTIVE COOLING AND HEATING BUS 5P.A and the HEAT AND COLDNESS REJECTION BUS 5P.5A, correspondingly, wherein the launched acoustic waves 5P.92A differ from the launches acoustic waves 5P.91A in phase on 180°. It further will be evident for a commonly educated person that the alternating current generated by the generator 5P.820A results in the origination and radiation of an electromagnetic wave characterized by the frequency f of the current alternation; and [0403] in the Case (B) SOUND DETECTION MODE, the ELEMENTAL DETECTOR OF SOUND 5P.0B functioning in the SOUND DETECTION MODE differs from TE element 1.0B functioning in the POWER GENERATION MODE and normally supplied with the ventilator 1.9B by that the load 1.6B (FIG. 1p Case (B) POWER GENERATION MODE) and the ventilator 1.9B, altogether are now replaced by an individual integrated circuit IC DETECTOR 5P.8B capable of detection AC originated by acoustic wave 5P.91B impacting the HEAT AND COLDNESS SOURCE BUS 5P.7B which, as a result, becomes subjected to alternating heating and cooling accompanying by the origination of alternating electric current. Again, optionally, the connection of the individual integrated circuit IC DETECTOR 5P.8B to the TE element 5P.B can be implemented using a transformer 5P.86B of the induced alternating electric current and voltage wherein the transformer 5P.86B: [0404] on the one hand, is connected to the metallic electrical contact pads 5P.41B and 5P.42B of an n-type (negative thermopower and electron carriers) semiconductor material 5P.1B and a p-type (positive thermopower and hole carriers) semiconductor material 5P.2B, correspondingly, and [0405] on the other hand, is connected to the individual integrated circuit IC DETECTOR 5P.810B, [0406] to separate the AC generated by the TE element 5P.B and the AC induced in the individual integrated circuit IC DETECTOR 5P.80B. It further will be evident for a commonly educated person that the induced alternating electric current originated in the thermoelectric element 5P.B, on the one hand, can be registered and/or recorded by any classic method, and on the other hand, results in the origination and radiation of an electromagnetic wave characterized by the frequency f of the induced current alternation that, in turn, can be detected using an RF receiving antenna.
As a consequence, from the point of view of functioning, the two cases: (A) and (B), differ as follows: [0407] In Case (A) SOUND LAUNCHING MODE, an ELEMENTAL SOURCE OF SOUND 5P.0A is capable of operation in a SOUND LAUNCHING MODE providing for audible sound and ultrasound launching; and, vice-versa, [0408] In Case (B) SOUND DETECTION MODE, an ELEMENTAL DETECTOR OF SOUND 5P.0B is capable of functioning in a SOUND DETECTION MODE providing for audible sound and ultrasound detection.
In view of the foregoing description referring to FIG. 5p, it will be evident for a commonly educated person that: [0409] In Relation to Accompanying Electro-Magnetic Waves, [0410] When operating in the sound launching mode, the ELEMENTAL SOURCE OF SOUND 5P.0A radiates electromagnetic waves of the same frequency as the frequency of the launched acoustic waves; in other words, the metallic electrical contact pad 5P.3A of the ELEMENTAL SOURCE OF SOUND 5P.0A operates as a transmitting antenna of electromagnetic waves, [0411] If the ELEMENTAL SOURCE AND DETECTOR OF SOUND 5P.0 is exposed to an electromagnetic wave of a certain frequency in the range between 20 Hz and 20 kHz (or higher), then the metallic electrical contact pad 5P.3A, as a receiving antenna detecting the electromagnetic wave, plays the role of the generator of alternating electric current or voltage 5P.820A providing the emf resulting in the generation of an acoustic wave (audible or ultrasound) of the same certain frequency; and [0412] If the ELEMENTAL DETECTOR OF SOUND 5P.0B is exposed to an acoustic wave of a certain frequency, the metallic electrical contact pad 5P.3B radiates an electromagnetic wave of the same certain frequency and so plays the role of a transmitting antenna allowing to detect the presence of sound using a sensor of electromagnetic waves wirelessly; [0413] In Relation To The Reversibility Of The ELEMENTAL SOURCE AND DETECTOR OF SOUND, [0414] If the manipulatable source of emf 5P.82A is shunted and the integrated circuit IC 5P.81A provides for the functionality of the individual integrated circuit IC DETECTOR 5P.8B, the ELEMENTAL SOURCE OF SOUND 5P.0A can be adapted to function as the ELEMENTAL DETECTOR OF SOUND 5P.0B in the Case (B) SOUND DETECTION MODE. This allows using the TE element 5P.A for operation as both: [0415] a source of sound when functioning in the sound launching mode, and [0416] a detector of sound when functioning in the sound detection mode; [0417] and [0418] In Relation To Phase-Inverter. [0419] In the detection mode, the opposite sides HEAT AND COLDNESS SOURCE BUS 5P.7B and HEAT AND COLD SINK BUS 5P.5B, both become heated and cooled alternatingly with the frequency f equal to the frequency of the impacting sound, wherein the phase of the temperature changes adjacent to the HEAT AND COLD SINK BUS 5P.58 differs from the phase of the temperature changes adjacent the HEAT AND COLDNESS SOURCE BUS 5P.7B on 1800. This, in particular, means that the TE element 5P.B functions as a phase-inverter which receives the acoustic wave 5P.91B impacting the HEAT AND COLDNESS SOURCE BUS 5P.7B and launches the acoustic wave 5P.92B propagating away from the HEAT AND COLD SINK BUS 5P.5B, wherein the phase of the launched acoustic wave 5P.92B differs from the phase of the received acoustic wave 5P.91B on 180°. It will be evident for a commonly educated person, that if now the individual integrated circuit IC DETECTOR 5P.8B is supplied by an amplifier providing for increasing an induced electric current, the TE element 5P.B becomes capable of functioning as an amplifier of acoustic waves which receives the acoustic wave 5P.91B impacting the HEAT AND COLDNESS SOURCE BUS 5P.7B and launches the amplified acoustic wave 5P.92B propagating away from the HEAT AND COLD SINK BUS 5P.5B, wherein the phase of the launched acoustic wave 5P.92B differs from the phase of the received acoustic wave 5P.91B on 180°.

Multi-Module Matrix Device

[0420] FIG. 5q, composed of two parts: (A) and (B), is a schematic illustration of components of a multi-module thermoelectric device.

[0421] The inventor points out, that, taking into account the foregoing description of THE BACKGROUND OF THE INVENTION referring to FIGS. 1c and 1d, it will be evident for a commonly educated person that a MULTI-MODULE SOURCE AND DETECTOR OF SOUND is feasible by aggregating a multiplicity of the ELEMENTAL SOURCES OF SOUND 5P.0A and ELEMENTAL DETECTORS OF SOUND 5P.0B such that the ELEMENTAL SOURCES OF SOUND 5P.0A and ELEMENTAL DETECTORS OF SOUND 5P.0B are connected into a sequential electric scheme and arranged to create and detect, correspondingly, the changes of the thermodynamic parameters of the ambient fluid in unison.

[0422] Moreover, an arrangement of the ELEMENTAL SOURCES OF SOUND 5P.0A and ELEMENTAL DETECTORS OF SOUND 5P.0B can be more sophisticated.

[0423] FIG. 5q (A) is a schematic isometry illustration of a fragment of planar arrangement 5Q.MATRIX of elemental thermoelectric elements 5Q.01, arranged in a plane (X, Y) in a system of coordinates (X, Y, Z) 5Q.0 and electrically mutually isolated.

[0424] FIG. 5q (B) is a schematic illustration of a cross-sectional cut of a multi-module thermoelectric device 5Q.DEVICE, called MATRIX SOURCE AND/OR DETECTOR OF SOUND, constructed according to the principles of the present invention.

[0425] The device MATRIX SOURCE AND/OR DETECTOR OF SOUND 5Q.DEVICE is composed of a multiplicity of N=N.sub.x×N.sub.y elemental TE devices 5Q.02, where N.sub.x and N.sub.y are numbers of the TE devices 5Q.02 arranged along the axes X and Y, correspondingly. Each of the N elemental TE devices 5Q.02 is similar to the elemental TE device 5P.0 functioning as an ELEMENTAL SOURCE AND/OR DETECTOR OF SOUND as described hereinabove in the subparagraph “in Relation To Phase-Inverter” referring to FIG. 5p. The N.sub.x×N.sub.y elemental TE devices 5Q.02 are arranged in a plane (X, Y) in a system of coordinates (X, Y, Z) 5Q.0, electrically mutually isolated, and have individual thermo-conductive buses, i.e. each of the N.sub.x×N.sub.y elemental TE devices 5Q.02 has individual both controller 5Q.08 and thermo-conductive bus 5Q.05 to be controlled individually. Each of the controllers 5Q.08 comprises an individual integrated circuit IC 5Q.81, manipulatable source of emf (for instance, generators of alternating electric current and voltage) 50.82, and, optionally, transformers 5Q.86 as described hereinabove referring to FIG. 5p. For the sake of simplicity of the schematic illustration: [0426] An arrangement along the axis X is shown only; and [0427] Points 5Q.03 symbolize that each of the numbers N.sub.x and N.sub.y can be much greater than shown.

Wherein:

[0428] Each of the N.sub.x×N.sub.y elemental TE devices 5Q.02 is the ELEMENTAL SOURCE OR DETECTOR OF SOUND 2P.0A or 2P.0B described hereinabove with the reference to FIG. 5p Case (A) SOUND LAUNCHING MODE or FIG. 5p Case (B) SOUND DETECTION MODE, correspondingly; and [0429] Each of the N.sub.x×N.sub.y individual integrated circuits IC 5Q.81, is individually controlled by a common controller-dispatcher 5Q.04.

[0430] In the launching mode, elemental acoustic waves, launched by the individually controlled N.sub.x×N.sub.y ELEMENTAL SOURCES OF SOUND 5Q.02 of the device MATRIX SOURCE AND/OR DETECTOR OF SOUND 5Q.DEVICE can differ in amplitude, phase, frequency, and delay, all controlled by the common controller-dispatcher 5Q.04. Thereby, the desired spatial interference map associated with the resulting acoustic wave composed of the elemental acoustic waves is feasible. For example, a well-known technique “phased array” can be applied to the elemental acoustic waves when using the matrix of the multiplicity of N.sub.x×N.sub.y ELEMENTAL SOURCES OF SOUND 5Q.02. Another useful property of the device MATRIX SOURCE AND/OR DETECTOR OF SOUND 5Q.DEVICE is that the loudness of the resulting launched sound can be controlled by the quantity of operating ELEMENTAL SOURCES OF SOUND 5Q.02. In practice, the device MATRIX SOURCE AND/OR DETECTORS OF SOUND 5Q.DEVICE comprising the big number N.sub.x×N.sub.y of ELEMENTAL SOURCES OF SOUND 5Q.02 provides for a big number of degrees of freedom for manipulation with characteristics of the elemental acoustic waves to create the desired waveform of the resulting launched acoustic wave. The big number of degrees of freedom allows for the coding and focusing of the resulting launched acoustic wave, wherein the device MATRIX SOURCE AND/OR DETECTORS OF SOUND 5Q.DEVICE remains relatively compact as not requiring big horns and is efficient comparing with classic speakers as not having moving components and so not originating concomitant turbulence.

[0431] In the detection mode, the N.sub.x×N.sub.y ELEMENTAL DETECTORS OF SOUND 5Q.02 of the device MATRIX SOURCE AND/OR DETECTOR OF SOUND 5Q.DEVICE are capable to detect a reached beam of elemental acoustic waves and release N.sub.x×N.sub.y associated elemental electrical signals and the common controller-dispatcher 5Q.04 is capable to superpose the released N.sub.x×N.sub.y elemental electrical signals. If the beam brings coded information due to that the N.sub.x×N.sub.y elemental acoustic waves differ in amplitude and/or phase and/or frequency and/or delay, then the N.sub.x×N.sub.y ELEMENTAL DETECTORS OF SOUND 5Q.02 release N.sub.x×N.sub.y different associated elemental electrical signals. Further, using the common controller-dispatcher 5Q.04 capable to superpose the released N.sub.x×N.sub.Y elemental electrical signals using a decoding algorithm, a decoding of the coded information becomes feasible.

[0432] In view of the foregoing description referring to FIG. 5p and FIGS. 2b (A) and (B) in combination with FIG. 1d, it will be evident for a commonly educated person that a three-dimensional matrix of a multiplicity of N.sub.x×N.sub.y×N.sub.z elemental TE devices 5Q.02, where N.sub.z is the number of the ELEMENTAL SOURCES OF SOUND 5Q.01 arranged along the axis Z in a manner shown in FIG. 1d, can be implemented to increase the reachable amplitude of the oscillating temperature difference δT using a smaller amplitude of the oscillating current density j when the elemental TE devices 5Q.02 function to launch acoustic waves.

Diversity of Uses for Multi-Module Matrix Devices

Detector of Sound

[0433] FIG. 5r is a schematic illustration of a multi-module thermoelectric device 5R.DEVICE, comprising a matrix of a multiplicity of N ELEMENTAL DETECTORS OF SOUND 5R.02, each of which comprises an individual integrated circuit controller as described hereinbefore referring to FIG. 5p, and a common controller-dispatcher 5R.04 capable to control the N ELEMENTAL DETECTORS OF SOUND 5R.02 individually by amplifying, and/or delays, and/or phase-shifting, and/or summing the associated induced individual electric currents. The multi-module thermoelectric device 5R.DEVICE has an overall shape of a plate having two sides: 5R.71 and 5R.72. When the side 5R.71 is exposed to an acoustic beam 5R.1.INPUT, a secondary acoustic wave 5R.2.OUTPUT is radiated from the side 5R.72 due to the Seebeck effect and the Peltier effect as a contribution to the resulting acoustic beam 5R.4.OUTPUT, as described hereinabove in the subparagraph “In Relation To Phase-Inverter” referring to FIG. 5p considering an alone ELEMENTAL SOURCE AND DETECTOR OF SOUND 5P.0. The two acoustic beams: 5R.1.INPUT and the secondary acoustic wave 5R.2.OUTPUT, are marked by opposite signs: “+” and “−” correspondingly, symbolizing the 180° phase-difference between the fronts of the two acoustic beams: 5R.1.INPUT and the secondary acoustic wave 5R.2.OUTPUT, adjacent to the two sides: 5R.71 and 5R.72, correspondingly. The thermoelectric device 5R.DEVICE is interpreted as a phase-inverter.

[0434] It will be evident to a commonly educated person that the acoustic beam 5R.1.INPUT acts on the side 5R.71 the thermoelectric device 5R.DEVICE not only due to the oscillating changes in temperature but also mechanically impacting the side 5R.71 of the thermoelectric device 5R.DEVICE due to the oscillating changes in static pressure. The mechanic impacts partially transmit the acoustic beam 5R.1.INPUT through the thermoelectric device 5R.DEVICE without the phase-inversion, thereby, resulting in the portion 5R.3.OUTPUT of the acoustic beam 5R.1.INPUT, which (the portion) is passed through the thermoelectric device 5R.DEVICE as a contribution 5R.3.OUTPUT to the resulting acoustic beam 5R.4.OUTPUT and radiated from the side 5R.72. As soon as the front of the contribution 5R.3.OUTPUT is not subjected to the phase-inversion and the velocity of acoustic waves in the solid material of the thermoelectric device 5R.DEVICE is much higher than the velocity of the acoustic waves in the air, the phase of the contribution 5R.3.OUTPUT radiated from the side 5R.72 is almost the same as the phase of the acoustic beam 5R.1.INPUT and so is reasonably indicated by sign “+”.

Optimized Detector of Sound

[0435] If the common controller-dispatcher 5R.04 of the thermoelectric device 5R.DEVICE provides for that the two contributions: [0436] the secondary acoustic wave 5R.2.OUTPUT, and [0437] the portion 5R.3.OUTPUT of the acoustic beam 5R.1.INPUT which (the portion) passed through the thermoelectric device 5R.DEVICE,
having the mutually opposite phases are such that the resulting acoustic beam 5R.4.OUTPUT has a zero amplitude, then the wave energy, brought by the acoustic beam 5R.1.INPUT, and the electric energy, consumed by both a multiplicity of individual integrated circuit controllers and the common controller-dispatcher 5R.04, altogether are transformed into the Joule heat and radiation of an electromagnetic wave which is accompanying the induced alternating current originated in the thermoelectric device 5R.DEVICE. This also means that there are suppressed waves reflected from the side 5R.71. Thus, the device 5R.DEVICE is adapted to function as a detector of sound, optimized to maximize the net-efficiency of sound detection.

Two-Stage Sound Amplifier

[0438] FIG. 5s is a schematic illustration of a two-stage sound amplifier 5S.DEVICE, constructed according to the principles of the present invention as a multi-module thermoelectric device, representing a cascade of two mutually electrically-separated thermoelectric devices: 5S-1.DEVICE and 5S-2.DEVICE, each of which is similar to the thermoelectric device 5R.DEVICE described hereinabove referring to FIG. 5r. The thermoelectric device 5S.DEVICE comprises a multiplicity of 2N ELEMENTAL DETECTORS OF SOUND 5S.02, each of which comprises an individual controller similar to the individual controller 5P.8A described hereinbefore referring to FIG. 5p, and a common controller-dispatcher 5S.04 capable to control the 2N ELEMENTAL DETECTORS OF SOUND individually by amplifying, and/or delays, and/or phase-shifting, and/or summing the induced individual electric currents.

[0439] When the side 58.71 is exposed to an impacting acoustic beam 5S.1.INPUT, the inner side 5S.72 is cooled and heated in anti-phase relative to the heating and cooling side 58.71. Further, a secondary acoustic wave 5S.2.OUTPUT is radiated from the side 5S.73 due to the Peltier effect as a contribution to the resulting acoustic beam 5S.4.OUTPUT. The two acoustic beams: impacting 5S.1.INPUT and the secondary acoustic wave 5S.2.OUTPUT, are marked by the same sign: “+”, symbolizing the zero phase difference between the fronts of the two acoustic beams: impacting 5S.1.INPUT and the secondary acoustic wave 5S.2.OUTPUT, adjacent to the two sides: 5S.71 and 5S.73, correspondingly.

[0440] Again, it will be evident to a commonly educated person that the impacting acoustic beam 5S.1.INPUT acts on the side 5S.71 of the thermoelectric device 5S.DEVICE not only due to the oscillating changes in temperature but also mechanically impacting the side 5S.71 of the thermoelectric device 5S.DEVICE due to the oscillating changes in static pressure. The mechanic impacts partially transmit the impacting acoustic beam 5S.1.INPUT through the thermoelectric device 5S.DEVICE without the phase-inversion, thereby, resulting in a contribution 5S.3.OUTPUT to the resulting acoustic beam 5S.4.OUTPUT radiated from the side 5S.73. As soon as the front of the contribution 5S.3.OUTPUT is not subjected to the phase-inversion and the wavelength of an acoustic wave in a solid material of the thermoelectric device 5S.DEVICE is much greater than the thickness 5S.03 of the thermoelectric device 5S.DEVICE, the phase of the contribution 5S.3.OUTPUT radiated from the side 58.73 is almost the same as the phase of the impacting acoustic beam 5S.1.INPUT and so is reasonably indicated by sign “+” as well. The two contributions: 5S.2.OUTPUT and 5S.3.OUTPUT, are in-phase, hence, in this case, the thermoelectric device 5S.DEVICE is adapted to function as a two-stage sound amplifier, optimized to maximize the net-efficiency of sound boosting.

[0441] It will be evident for a commonly educated person that a phonendoscope and hearing aid, both can be supplied with the two-stage sound amplifier embodied as the thermoelectric device 5S.DEVICE.

Acoustic Wireless Charger

[0442] FIG. 5t is a schematic illustration of a communication system 5T.SYSTEM, constructed according to the present invention. The communication system 5T.SYSTEM comprises: [0443] a multi-module thermoelectric device 5T.TX-ANTENNA, having a matrix composed of a multiplicity of N ELEMENTAL SOURCES OF SOUND 5T.02A functioning in the SOUND LAUNCHING MODE and a common controller-dispatcher 5T.04A, and [0444] a multi-module thermoelectric device 5T.RX-ANTENNA, composed of a matrix composed of a multiplicity of N ELEMENTAL DETECTORS OF SOUND 5T.02B functioning in the SOUND DETECTION MODE and a common controller-dispatcher 5T.04B.
While the common controller-dispatcher 5T.04A provides for an implementation of the technique phased array applied to the matrix of the multiplicity of N ELEMENTAL SOURCES OF SOUND 5T.02A to form an acoustic beam 5T.1.INPUT directed to the multi-module thermoelectric device 5T.RX-ANTENNA, the common controller-dispatcher 5T.04B provides for the operation of the sound detecting multi-module thermoelectric device 5T.RX-ANTENNA similar to the operation of the multi-module thermoelectric device 5R.DEVICE described hereinabove in subparagraph “Optimized Detector Of Sound” referring to FIG. 5r, namely, such that the two contributions 5T.2.OUTPUT and 5T.3.OUTPUT (both analogous to the aforementioned two contributions 5R.2.OUTPUT and 5R.3.OUTPUT) having the mutually opposite phases, such that the resulting acoustic beam 5T.4.OUTPUT has zero amplitude (analogously to the aforementioned resulting acoustic beam 5R.4.OUTPUT). The IC DETECTOR 5T.8B is similar to the IC DETECTOR 5P.8B (FIG. 5p) but is now specified as having a DIODE BRIDGE 5T.81B and a RECHARGEABLE BATTERY 5T.81B. An induced alternating electric current generated in the IC DETECTOR 5T.8B moves through the DIODE BRIDGE 5T.81B and charges the RECHARGEABLE BATTERY 5T.81B, thereby, cumulating the electric energy, which is acquired from the wave energy of the detected acoustic beam 5T.1.INPUT. Thus, the communication system 5T.SYSTEM represents an acoustic wireless charger.

[0445] To estimate the practical feasibility of the acoustic wireless charger, consider the multi-module thermoelectric device 5T.TX-ANTENNA having a linear size of several times greater than 1 mm and the acoustic beam 5S.1.INPUT which is composed of acoustic waves at the ultrasound frequency of 340 kHz. In this case, [0446] the wavelength of the ultrasound is estimated as 1 mm; and [0447] half of the time-period allowing for the temperature oscillation is 0.5×τ.sub.340 kHZ≈1.5×10.sup.−6 sec and the reachable amplitude of the temperature difference is, approximately, of 1.8×10.sup.−6 K that corresponds to SPL=SDL=STL level of 70 dB.
The phased array technique is applicable to the wavelength of 1 mm, as the linear size of the multi-module thermoelectric device 5T.TX-ANTENNA is assumed of several times greater than 1 mm. Normally, the net-efficiency of the electrical scheme of the IC DETECTOR 5T.8B is higher than 50%. Taking into account that the wave power is proportional to squired frequency; if the charging energy is further destined to generate a 2 kHz sound, a reachable SPL of the 2 kHz sound is about 109 dB. The estimation shows that the acoustic wireless charger can be sufficiently efficient when charging the multi-module thermoelectric device 5T.RX-ANTENNA wirelessly from 1 m distance using the 340 kHz ultrasound.

[0448] In view of the foregoing description referring to FIGS. 5q, 5p, 5r, 5s, and 5t, it will be evident for a person skilled in the art that, if the multi-module thermoelectric device 5T.RX-ANTENNA operates in a passive mode without the functioning of the dispatcher 5T.04B, then the magnitudes of the contributions 5T.2.OUTPUT and 5T.3.OUTPUT, both are neither controlled nor optimized and so a non-zero resulting acoustic beam 5T.3.OUTPUT determines a reduced net-efficiency of the acoustic wireless charger.

Convergent-Divergent Jet-Nozzle

[0449] FIG. 6a, composed of two parts: (A) Shape and (B) Graph, is a schematic illustration of a modified convergent-divergent jet-nozzle.

[0450] FIG. 6a (A) Shape shows schematically a sectional view of the modified convergent-divergent jet-nozzle 610 in a sagittal plane. The modified convergent-divergent jet-nozzle 610 having a shaped tunnel is applied to accelerate a laminarly flowing compressed and hot compressible-expandable fluid 611. In contrast to the prior art convergent-divergent nozzles, which are passively adapted to only certainly-given velocity and thermodynamic parameters (and are not adapted to arbitrary velocity and thermodynamic parameters) of an incoming fluid flow to provide for a laminar flow as described hereinabove in subparagraph “De Laval Effect” referring to FIG. 1c, the modified convergent-divergent jet-nozzle 610, constructed according to an exemplary embodiment of the present invention, allows for the implementation of either the enhanced Venturi effect or the enhanced de Laval jet-effect, each providing a laminar acceleration of fluid flow 611 for a wide range of velocities u.sub.in and thermodynamic parameters: the static pressure P.sub.in, absolute temperature T.sub.in, and mass density ρ.sub.in, of entering fluid flow 611 at an open inlet 617. The shaped tunnel of the modified convergent-divergent jet-nozzle 610 has opposite walls 6A.WALLS, which are either formed by or at least supplied with a surface matrix 6A.MATRIX of densely-arranged elemental thermoelectric devices 6A.TED. The triplet of dots 6A.DOT symbolizes that the elemental thermoelectric devices 6A.TED are arranged unbrokenly. The surface matrix 6A.MATRIX is analogous to the planar matrix 5Q.MATRIX of elemental thermoelectric devices 5Q.02 described hereinabove referring to FIG. 5q, but now is aligned to the opposite walls 6A.WALLS's shape. The opposite walls 6A.WALLS are shaped, for the sake of concretization and without loss of generality, axis-symmetrically around an imaginary sagittal x-axis 615, as a convergent funnel 612 comprising an open inlet 617 having a cross-sectional area A.sub.in and diameter D.sub.in, narrow throat 613 comprising point 618 of the narrowest cross-section cross-sectional area A.sub.th and diameter D.sub.th, and divergent exhaust tailpipe 614 having an open outlet 619 having a cross-sectional area A.sub.ou and diameter D.sub.ou. When moving through the smoothly shaped tunnel having controllably heated and/or cooled walls, the fluid stream 611 becomes subjected, on the one hand, to change in cross-sectional area and, on the other hand, to forcedly established temperature distributed due to controllably functioning densely-arranged elemental thermoelectric devices 6A.TED. The linear sizes: D.sub.in, D.sub.th, D.sub.ou may differ from associated linear sizes of the mentioned prior art passively adapted convergent-divergent nozzle, passively adapted to only certainly-given velocity and thermodynamic parameters of the incoming fluid flow 611, on a thickness of a boundary layer nearby the opposite walls 6A.WALLS. Thus, the thickness of the boundary layer near each of the walls 6A.WALLS plays the role of a tolerance allowing for a degree of freedom to manipulate with the forcedly establishing of the temperature using the thermoelectric devices 6A.TED. The surface matrix 6A.MATRIX of the thermoelectric devices 6A.TED provides for controllably distributed temperature along the sagittal axis 615 having a distance parameter x. The varying cross-sectional area of the smoothly shaped tunnel is characterized by a cross-sectional area profile function A(x) of x interrelated with functions u(x) and T(x) of x representing profiles of the fluid flow's headway velocity and absolute temperature, correspondingly, along the tunnel length, wherein the thermoelectric devices 6A.TED providing for a degree of freedom to interrelate the functions A(x), u(x), and T(x) by a condition of flow continuity expressed as:

[00016] $\begin{matrix} A (x) = \frac{A_{*} \sqrt{(γ - 1) RT (x)}}{u (x)} {(\frac{2}{γ + 1} + \frac{{(u (x))}^{2}}{(γ + 1) RT (x)})}^{\frac{γ + 1}{2 (γ - 1)}}, & Eq . 6.0 \end{matrix}$

where A.sub.* is a constant, γ is an adiabatic compressibility parameter of the flowing fluid, and R is a specific gas constant characterizing the fluid flow, wherein the functions u(x) and T(x) both are gradually-smoothed monotonic, wherein: [0451] the gradually-smoothed monotonic function of the absolute temperature T(x) is determined by: [0452] the absolute temperature T.sub.in the fluid flow at the open inlet; [0453] the temperature change δT.sub.0(x) interrelated with adiabatic compression-expansion occurred due to an adiabatic action of the Coanda-effect, in turn, determined by a curvature of the stationary geometrical configuration of the tunnel; and [0454] forcedly established temperature contribution δT.sub.1(x) to the absolute temperature T(x) along the boundary layers subjected to controllable heating and/or cooling action of the thermoelectric devices 6A.TED, [0455] such that T(x)=T.sub.in+δT.sub.0(x)+δT.sub.1(x), and [0456] the gradually-smoothed monotonic function of the headway velocity u(x) is determined by the certain headway velocity u.sub.in of the fluid flow 611 at the open inlet, convective headway acceleration resulting in a velocity gradient along the tunnel length as the fluid flow 611 is subjected to the adiabatic Coanda-effect, and controllable headway acceleration occurred due to controllable heating and/or cooling action of the thermoelectric devices 6A.TED.
The condition of flow continuity Eq. (6.0) is correct as for relatively slow motions corresponding to low M-velocities, lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} as well as for relatively fast motions corresponding to high M-velocities, higher than the specific M-velocity.

[0457] The constant A.sub.* is a characteristic cross-sectional area defined for a certain fluid; the characteristic cross-sectional area A.sub.* is a hypothetically-minimal reachable by a portion of the fluid when the portion of the fluid is convectively accelerated in an adiabatic process, according to the equation of continuity. Considering the case: [0458] when the minimal cross-sectional area A.sub.th of the narrow throat is greater than the hypothetically-minimal reachable constant A.sub.*, there are no critical condition points within the tunnel and the convergent-divergent nozzle 610 plays the role of a Venturi pipe providing for the Venturi effect; and [0459] when the minimal cross-sectional area A.sub.th of the narrow throat is lesser than or equal to the hypothetically-minimal reachable constant A.sub.* (A.sub.th≤A.sub.*), the flowing fluid 611, being subjected to a convective acceleration in an adiabatic process and crossing the minimal cross-sectional area A.sub.th of the narrow throat 613, is capable of reaching at most the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} (which is a characteristic of the fluid as well) and so the convergent-divergent nozzle 610 plays the role of a de Laval jet-nozzle providing for the de Laval jet-effect; wherein the condition A.sub.th<A.sub.* contradicts the condition of flow continuity (6.0) and thereby the de Laval jet-effect is not optimized on the criterion of laminar motion of the fluid flow 611.

[0460] Considering the case, when the modified convergent-divergent jet-nozzle 610 is destined to trigger the enhanced de Laval jet-effect recognized by a laminar motion of the fluid flow 611, the narrow throat 613 should be narrow sufficient such that the minimal cross-sectional area A.sub.th is the hypothetically-reachable minimal cross-sectional area A.sub.* providing the “critical condition” point 618 where the temperature-dependent M-velocity gradually reaches the value of the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. In practice, to provide the strict condition A.sub.th=A.sub.* using a passively adapted convergent-divergent nozzle is almost impossible. The surface matrix 6A.MATRIX of the densely-arranged elemental thermoelectric devices 6A.TED allows for such a control of the temperature contribution δT.sub.1(x) that the resulting gradually-smoothed monotonic function of the absolute temperature T(x)=T.sub.in+δT.sub.0(x)+δT.sub.1(x) satisfies the condition Eq. (6.0).

[0461] The degree of freedom to manipulate with the function T(x) via the function δT.sub.1(x) to satisfy the condition of flow continuity Eq. (6.0) provides for that the combined action on the fluid stream 611 provides for gradually-smoothed monotonic changes preventing jumps of the fluid stream headway velocity u(x) and all of the thermodynamic parameters of the fluid: the static pressure P(x), the absolute temperature T(x), and the mass density ρ(x), thereby, providing the following beneficial features: [0462] smoothing (or, preferred, linearizing) of the fluid stream headway velocity, providing suppression of the undesired flow turbulence; [0463] smoothing (or, preferred, linearizing) of the fluid stream static pressure, providing suppression of the undesired Mach waves and, thereby, suppression of nearby body vibrations; [0464] smoothing (or, preferred, linearizing) of the fluid stream mass density, providing suppression of the undesired flow disturbances accompanied by shock waves; [0465] smoothing of the flowing fluid absolute temperature, providing suppression of adjacent surface tensions; and [0466] smoothing (or, preferred, linearizing) of the flowing fluid M-velocity, providing a trade-off of suppressions of undesired all: the turbulence, vibrations, shock and Mach waves, and surface tensions.
The relatively fast fluid flow 611 provides for conditions allowing to exclude using a powerful ventilator, normally, accompanying thermoelectric devices.

[0467] FIG. 6a (B) Graph, in conjunction with FIG. 6a (A) Shape, is a schematic graphic illustration of the distribution of the flowing fluid 611's four mutually-scaled parameters: headway velocity 620.u, static pressure 630.P, absolute temperature 640.T, and M-velocity 650.M along the length of nozzle 610, constructed according to the principles of a preferred embodiment of the present invention to provide a linear function of M-velocity 650.M of the flowing fluid. The narrowest cross-section of the narrow throat 613 provides the “critical condition” point 618. Compressed and hot fluid 611 flows through the narrow throat 613, where the velocity picks up 621 such that M-velocity 650.M reaches the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} 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 the narrow 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 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 associated with the classic prior art rocket nozzle 100 of FIGS. 1c, 1d. The smoothed change of static pressure 630.P provides suppression of unwanted in general, acoustic waves, and, in particular, Mach waves. In practice, the suppression of Mach waves provides suppression of undesired vibrations that, in particular, especially important for fast accelerating vehicles.

[0468] It will be evident for a person skilled in the art that: [0469] If, in a particular case, the geometrical configuration of the shaped tunnel is such that, for a certain velocity u.sub.in of a fluid stream 611 at the inlet 617 and certain thermodynamic parameters, the condition of flow continuity Eq. (6.0) is satisfied without the forcedly establishing temperature distribution, then the condition of flow continuity (6.0) reverts into the prior art equation Eq. (1.a) described hereinabove in the subparagraph “De Laval Effect” referring to FIG. 1c; [0470] If, in general, the geometrical configuration of the shaped tunnel is gradually-smoothed or, in a particular case, the geometrical configuration of the shaped tunnel is trivial cylindrical, wherein, in any case, the linear size of the narrow throat (for instance, the diameter D.sub.th) is of the same order of value as the thickness of the boundary layer near each of the walls 6A.WALLS, and if the fluid flow having the absolute temperature T.sub.in corresponding to the left point of the curve 640.T enters the tunnel with velocity u.sub.in corresponding to the left point of the curve 620.u, then a forcedly established temperature profile along the shaped tunnel corresponding to the curve 640.T provides for: [0471] the fluid stream static pressure decrease corresponding to the curve 630.P, [0472] the fluid stream velocity increase corresponding to the curve 620.u, and [0473] the fluid stream M-velocity linear increase corresponding to the curve 650.M; and [0474] In practice, if a substantial acceleration is desired, hardly, it is preferred to use the mentioned trivial cylindrical geometrical configuration assuming δT.sub.0(x)=0 and provide the desired temperature distribution T(x) using the forcedly established temperature δT.sub.0(x) only, but it is preferred to use at least an almost adapted geometrical configuration already providing the temperature distribution T.sub.in+δT.sub.0(x) and use the degree of freedom to compensate for a lack of temperature distribution δT.sub.1(x) using the densely-arranged elemental thermoelectric devices 6A.TED.

[0475] A convergent-divergent jet-nozzle, constructed applying the condition of flow continuity Eq. (6.0) accompanied by the satisfying condition of the smoothed thermodynamic parameters of the flowing fluid 611 according to an exemplary embodiment of the present invention, allows the use of the enhanced de Laval jet-effect to accelerate incoming compressed and hot airstream 611 moving with low M-velocities to obtain outflowing 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.

[0476] 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 the gradualness of u(x), T(x), P(x), ρ(x), and M(x), for different preferred optimizations of the convergent-divergent shape of a tunnel.

[0477] Namely, the conditions, providing laminarity of the airstream motion, are: [0478] if suppression of disturbances, which are capable of growing into turbulence, is the most preferred, then u(x) should be given as the linear function u(x)=ū(x)=u.sub.*+α.sub.u(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 velocity spatial distribution, i.e. α.sub.u=∂ū(x)/∂x, and the function δT.sub.1(x) should be established such that the function T(x)=T.sub.in+δT.sub.0(x)+δT.sub.1(x) would satisfy to the condition of flow continuity Eq. (6.0); wherein because the higher the velocity of the moving stream 611 the shorter the possible response time of the TE devices 6A.TED: up to 2.5×10.sup.−5 sec and shorter (as described hereinabove referring to FIG. 5p), [0479] the TE devices occupying a path of 5 mm are capable of preventing a local temperature jump, and so preventing an origination of a turbulent vortex bigger than 5 mm in a boundary layer moving with the velocity of 200 m/sec, and [0480] a hypersonic laminar flow (for instance, of 3500 m/sec) can be controlled in a long tunnel; [0481] if suppression of Mach waves and body vibrations are the most preferred, then the function δT.sub.1(x) should be established such that the temperature-dependent function M(x)=u(x)/√{square root over (γR×[T.sub.in+δT.sub.0(x)+δT.sub.1(x)])} becomes given as the function M(x)=√{square root over (2{[P.sub.0/P(x)].sup.(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; [0482] if the suppression of temperature jumps is the most preferred, then the function δT.sub.1(x) should be established such that the function [T.sub.in+δT.sub.0(x)+δT.sub.1(x)] is a linear function T(x) 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; [0483] if suppression of shock waves is the most preferred, then the function δT.sub.1(x) should be established such that the temperature-dependent function M(x)=u(x)/√{square root over (γR×[T.sub.in+δT.sub.0(x)+δT.sub.1(x)])} becomes given as the function M(x)=√{square root over (2{[ρ.sub.0/ρ(x)].sup.(γ-1)−1}/γ)}, where ρ(x) is a linear function of the fluid mass density vs. x-coordinate: ρ(x)=ρ.sub.*+α.sub.ρ(x−x.sub.*), ρ.sub.* is the mass density of said flowing fluid at the critical condition point x.sub.*, and α.sub.ρ=∂ρ(x)/∂x is a constant gradient of the fluid mass density distributed along the x-axis within a specially shaped tunnel; and [0484] if a trade-off between all the mentioned suppressions is preferred; then the function δT.sub.1(x) should be established such that the temperature-dependent function M(x)=u(x)/√{square root over (γR×[T.sub.in+δT.sub.0(x)+δT.sub.1(x)])} becomes a linear function 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. α.sub.M=∂M(x)/∂x.
It will become further evident for a person, who has studied the present invention, that it is possible to compose a multi-stage nozzle composed of N nozzles each of which satisfies the condition of flow continuity Eq. (6.0); wherein the N nozzles, enumerated from 1 to N, are united together to join the N tunnels associated with the N nozzles, correspondingly, such that each of the N tunnels is a fragment of a resulting unbroken tunnel formed thereby as a whole; an n-th fragment, where n is an integer between 1 and N: 1≤n≤N, has the varying cross-sectional area characterized by a cross-sectional area profile function A.sub.n(x) of x expressed as an individual condition of flow continuity:

[00017] $A_{n} (x) = \frac{A_{* n} \sqrt{(γ - 1) {RT}_{n} (x)}}{u_{n} (x)} {(\frac{2}{γ + 1} + \frac{{(u_{n} (x))}^{2}}{(γ + 1) {RT}_{n} (x)})}^{\frac{γ + 1}{2 (γ - 1)}}$

where A.sub.*n is n-th constant, and the functions u.sub.n(x) and T.sub.n(x) are representing profiles of the fluid flow's headway velocity and absolute temperature, correspondingly, along the n-th fragment of the resulting unbroken tunnel length; the resulting unbroken tunnel as a whole is either converging, or divergent, or convergent-divergent, or two-stage convergent-divergent; or multi-stage convergent-divergent; wherein piecewise-monotonic profile functions u(x), P(x), ρ(x), T(x), and M(x), composed of associated gradually-smoothed monotonic profile functions concatenated together, all remain gradually-smoothed along the resulting unbroken tunnel as a whole, thereby, the multi-stage nozzle is applicable to convey: [0485] in general, laminar flow to solve the problem of originated turbulence, and [0486] in particular, tiny portions of the fluid associated with an acoustic wave propagating within and along the tunnel to solve the problem of sound power dissipation.
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 condition of flow continuity Eq. (6.0) and at least one of the aforementioned conditions for the functions u(x) and T(x), thereby, providing laminarity of the flow portion motion.

[0487] In view of the foregoing description referring to FIG. 6a, it will be evident to a person skilled in the art that: [0488] 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 condition of laminar flow should be corrected becoming different from the condition of flow continuity Eq. (6.0) by a component depending on the gravitational acceleration g, namely:

[00018] $\begin{matrix} \frac{A}{A_{*}} = \frac{M_{*}}{M} {(\frac{1 + \frac{γ}{2} M^{2} + \frac{g Δ h}{R T}}{1 + \frac{γ}{2} M_{*}^{2}})}^{\frac{γ + 1}{2 (γ - 1)}}, & Eq . (6.0 a) \end{matrix}$ [0489] 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, the use of the condition of flow continuity in the form of Eq. (6.0) becomes justified; [0490] 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 condition of flow continuity Eq. (6.0) is not a constant but varies with the changes of the partial deep-stagnation pressure-a δP.sub.a; [0491] If the flowing molecular fluid is an ionized gas, i.e. plasma, controlled by an external magnetic field, then the specifically shaped walls 6A.WALLS of the tunnel can be imaginary, formed by streamlines of the flowing plasma subjected to and controlled by an action of the magnetic field; [0492] When the shape of the tunnel is not completely optimized on one of the mentioned criteria either: [0493] smoothing of the flowing fluid velocity, or [0494] smoothing of the flowing fluid M-velocity, or [0495] smoothing of the flowing fluid static pressure, or [0496] smoothing of the flowing fluid temperature, or [0497] smoothing of the flowing fluid mass density, [0498] at least because the tunnel shape must be adapted to the initial velocity and thermodynamic parameters of the laminarly flowing hot-and-compressed compressible-expandable fluid 611, any of the desired optimizations is reachable by controlling the elemental TE devices 6A.TED of the surface matrix 6A.MATRIX while the densely-arranged elemental TE devices 6A.TED are capable of providing for the desired temperature at the locations corresponding to the elemental TE devices 6A.TED due to the Peltier effect. Moreover, the forcedly established desired distributed temperature prevents the “separation-points” [like 1G.46 of FIG. 1g Scheme (D)] of breaking or jumping of all: the headway velocity, the static pressure, the absolute temperature, and the mass density nearby the tunnel walls 6A.WALLS. The feasibility of such a control is supported by the property of flowing fluid moving adjacent to an airfoil wall described hereinabove referring to FIG. 1g Graph (D). Namely, on the one hand, a tiny portion of the flow, moving adjacent to a solid surface, can be heated or cooled by the solid surface when getting the temperature of the solid surface and, on the other hand, a big portion of the flow, moving farther from the solid surface, is capable of removing of excess heat or reverting the reduced portion of the heat, correspondingly; wherein, on the one hand, the faster flow the faster heat-transmitting, and, on the other hand, the tiny portion always has the temperature of the solid surface. In other words, it is possible to optimize the fluid stream within the shaped tunnel by changing the temperature of the fluid stream using the Peltier effect originated by the surface matrix 6A.MATRIX of the elemental TE devices 6A.TED built-in into the specifically shaped walls 6A.WALLS of the tunnel; [0499] As the surface matrix 6A.MATRIX of the elemental TE devices 6A.TED, built-in into the specifically shaped walls 6A.WALLS of the tunnel, is capable to transform the temperature differences between: [0500] on the one hand, the inner side of the specifically shaped walls 6A.WALLS which contacts with the fluid stream 611 within the tunnel, and [0501] on the other hand, the outer side of the tunnel, which contacts with the ambient fluid, [0502] into electricity due to the Seebeck effect, it becomes possible to optimize the shape of the tunnel such that to take into account the change in temperature caused due to pumping out the heat energy of the fluid stream 611 to produce the controllably consumed electric power; wherein the optimization is such that to maintain the laminarity of the fluid stream 611 within the tunnel and, thereby, to provide efficient functionality of the elemental TE devices 6A.TED use; [0503] and [0504] The parameter γ is varying when the chemical composition of the flowing fluid is changing.

De Laval Retarding-Effect

[0505] FIG. 6b, composed of two parts: (A) Shape and (B) Graph, is a schematic illustration of an inverse convergent-divergent jet-nozzle.

[0506] FIG. 6b (A) Shape illustrates a sectional view of the inverse convergent-divergent jet-nozzle 650 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 the modified convergent-divergent jet-nozzle 610, shown in FIG. 6a (A) Shape, and oriented to oncoming fluid-flow 651 in the back direction. Namely, the shaped tunnel of the inverse convergent-divergent jet-nozzle 650 has opposite walls 6B.WALLS, which are either formed by or at least supplied with a surface matrix 6B.MATRIX of densely-arranged elemental thermoelectric devices 6B.TED. The triplet of dots 6B.DOT symbolizes that the elemental thermoelectric devices 6B.TED are arranged unbrokenly. A convergent funnel 652 having open inlet is as inverse divergent exhaust tailpipe 614 (FIG. 6a (A) Shape), 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.

[0507] FIG. 6b (Graph), in conjunction with FIG. 6b (A) Shape, is a schematic graphic illustration of the distribution of the fluid 651's three parameters: headway velocity 660.u, static pressure 670.P, and temperature 680.T along the length of nozzle 650 calculated according to the condition of flow continuity Eq. (6.0) to provide a linear decrease in M-velocity of the flow. The linear function of M-velocity is not shown here.

[0508] The narrowest cross-section of the throat 653 provides the “critical condition” point 658, triggering the inverse de Laval jet-effect, according to the condition of flow continuity Eq. (6.0), 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 an 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.P provides suppression of unwanted Mach waves. In practice, the suppression of Mach waves provides suppression of undesired vibrations that, in particular, especially important for a fast decelerating flying vehicle.

[0509] In view of the foregoing description referring to FIG. 6b, 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 6B.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 and to forcedly established distributed temperature 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.*.

[0510] In view of the foregoing description referring to FIGS. 6a and 6b, 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.

[0511] 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: [0512] 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.*; [0513] a de Laval low M-velocity is defined as an M-velocity lower than the specific M-velocity M. and high sufficient to reach the specific M-velocity M.sub.* at the critical condition point x.sub.*; [0514] 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 [0515] a de Laval M-velocity is at least one of the de Laval low M-velocity and the de Laval high M-velocity.

[0516] In view of the foregoing description referring to FIG. 6b, 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 conformity of the cross-sectional area of the open inlet and the forcedly established temperature distribution 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 the open inlet and the forcedly established temperature distribution, according to the condition of flow continuity Eq. (6.0), providing conformity of the thermodynamic conditions at the open inlet with the variable M-velocity of the entering flowing fluid. This may become important, for example, to suppress vibrations of a fast slowing vehicle.

Two-Stage Convergent-Divergent Jet-Nozzle

[0517] FIG. 6c 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 comprises an inner tunnel, constructed according to the principles of a preferred embodiment of the present invention, having opposite walls 6C.WALLS, which are either formed by or at least supplied with a surface matrix 6C.MATRIX of densely-arranged elemental thermoelectric devices 6C.TED. The triplet of dots 6C.DOT symbolizes that the elemental thermoelectric devices 6C.TED are arranged unbrokenly. The inner tunnel comprises 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.

[0518] 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. Then, 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.

[0519] The first and second convergent-divergent stages of the inner tunnel are characterized by cross-sectional area profile functions A.sub.1(x) and A.sub.2(x) of distance parameter x, correspondingly, such that:

[00019] $\begin{matrix} A_{1} (x) = \frac{A_{* 1} \sqrt{(γ - 1) {RT}_{1} (x)}}{u_{1} (x)} {(\frac{2}{γ + 1} + \frac{{(u_{1} (x))}^{2}}{(γ + 1) {RT}_{1} (x)})}^{\frac{γ + 1}{2 (γ - 1)}} & Eq . (6.1) \\ A_{2} (x) = \frac{A_{* 2} \sqrt{(γ - 1) {RT}_{2} (x)}}{u_{2} (x)} {(\frac{2}{γ + 1} + \frac{{(u_{2} (x))}^{2}}{(γ + 1) {RT}_{2} (x)})}^{\frac{γ + 1}{2 (γ - 1)}} & Eq . (6.2) \end{matrix}$

where A.sub.*1 and A.sub.*2 are the minimal cross-sectional areas of the first-stage narrow throat 693 and the second-stage narrow throat 696, correspondingly, and the functions, on the one hand, u.sub.1(x) and T.sub.1(x) and, on the other hand, u.sub.2(x) and T.sub.2(x) u.sub.2(x) are representing profiles of the fluid flow headway velocities and absolute temperatures in the first and second convergent-divergent stages, correspondingly, along the inner tunnel length. The equations Eq. (6.1) and Eq. (6.2) are particular cases of the condition of flow continuity Eq. (6.0) described hereinbefore with references to FIGS. 6a and 6b, correspondingly.

[0520] 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 the condition of flow continuity Eq. (6.0).

[0521] Thereby, two-stage convergent-divergent jet-nozzle 690 operates as a jet-booster based on the enhanced de Laval jet-effect launching outflowing jetstream 699, which is faster than the 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.

[0522] In view of the foregoing description referring to FIGS. 6a, 6b, and 6c in combination with the foregoing description referring to FIGS. 5p and 5q, it will be evident to a person skilled in the art that, if a tunnel is preliminary optimized for a certain fluid, laminarly flowing within the tunnel with certain distributions of velocity and thermodynamic parameters, but, actually, the fluid is characterized by other thermodynamic parameters and enters the tunnel with another velocity, it remains possible to optimize the fluid stream within the shaped tunnel by forced establishing the temperature distribution of the fluid stream using the Peltier effect originated by a surface matrix of densely arranged elemental TE devices built-in into the walls of the tunnel.

Optimal Implementation of Convergent-Divergent Jet-Nozzle

[0523] FIG. 7 shows comparative graphs 700 for the dependencies of the nozzle tunnel extension ratio vs. the airflow M-velocity in an adiabatic process, calculated, on the one hand, using the classical model described, in particular, in D11 and, on the other hand, suggested in prior arts A01, A02, and A03 equation Eq. (1.a), 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 in an adiabatic process 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 classical equations 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 of an adiabatic motion, calculated using the prior art equation Eq. (1.a) derived from the specified equations of fluid motion in an adiabatic process described in A01, A02, and A03. 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.

[0524] One of the primary ideas of the present invention is that the desired improved dependence 704 is reachable using an arbitrary smoothly shaped tunnel if the temperature distribution along the tunnel's walls is forcedly controlled to satisfy the condition of flow continuity Eq. (6.0).

[0525] Therefore, a convergent-divergent jet-nozzle, constructed according to an exemplary embodiment of the present invention, allows for a controllably-increased efficiency of the jet-effect for use at high-subsonic, transonic, supersonic, and hypersonic velocities that can be applied to rocket nozzle design.

[0526] Taking into account The Bernoulli Theorem written in the form via M-velocity:

[00020] $\begin{matrix} \frac{T_{0}}{T} = {(\frac{P_{0}}{P})}^{\frac{γ - 1}{γ}} = {(\frac{ρ_{0}}{ρ})}^{γ - 1} = 1 + M^{2} \frac{γ}{2}, & Eq . (7.1) \end{matrix}$

[0527] where P.sub.0, ρ.sub.0, and T.sub.0 are so-called stagnation thermodynamic parameters: the static pressure, the mass density, and the absolute temperature, and M is the M-velocity, one can derive conditions for the stagnation thermodynamic parameters and the thermodynamic parameters of the fluid flow: P.sub.e, ρ.sub.e, and T.sub.e are so-called stagnation thermodynamic parameters: the static pressure, the mass density, and the absolute temperature, all at the exhaust-nozzle outlet to design an improved convergent-divergent nozzle to originate the enhanced de Laval effect. The exhaust-nozzle outlet M-velocity M.sub.e is bonded with the ratios P.sub.0/P.sub.e and T.sub.0/T.sub.e as follows:

[00021] $\begin{matrix} M_{e} = \sqrt{\frac{2}{γ}} \sqrt{{(\frac{P_{0}}{P_{e}})}^{\frac{γ - 1}{γ}} - 1} & Eq . (7.1 a) \\ \frac{P_{0}}{P_{e}} = {(\frac{2 + γ M_{e}^{2}}{2})}^{\frac{γ}{γ - 1}} & Eq . (7.1 b) \\ \frac{T_{0}}{T_{e}} = (\frac{2 + γ M_{e}^{2}}{2}) & Eq . (7.1 c) \\ \frac{ρ_{0}}{ρ_{e}} = {(\frac{2 + γ M_{e}^{2}}{2})}^{\frac{1}{γ - 1}} & Eq . (7.1 d) \end{matrix}$

[0528] In contrast to a frequently used condition, 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 Eq. (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 Eq. (7.1c) says that, on the one hand, to obtain the de Laval jet-effect for air utilizing a nozzle tunnel having an 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 can 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. 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 for an optimal implementation and efficient use of an enhanced jet-effect at de Laval M-velocities.

Use of Optimal Convergent-Divergent Jet-Nozzle

[0529] In view of the foregoing description referring to FIGS. 6a, 6b, and 6c in combination with the description of sub-paragraphs “Horn as Sound-Booster” referring to prior art FIG. 1n and “External Ear as Sound Booster” referring to prior art FIG. 1L, it will be evident to a person skilled in the art that: [0530] an optimized at least one of converging, divergent, convergent-divergent, and two-stage convergent-divergent nozzle can play the role of an enhanced acoustic waveguide capable to: [0531] reduce a turbulent component of fluid motion accompanying acoustic waves and causing dissipation of a propagating sound; and [0532] amplify the intensity of acoustic waves at the expense of both the heat energy and the turbulence of fluid and so to boost the loudness of sound; [0533] and [0534] the exponentially-divergent horn n.C1 of gramophone 1n.C (FIG. 1n) functions as the divergent exhaust tailpipe 614 of the convergent-divergent nozzle 610 (FIG. 6a), but not optimized according to the condition of flow continuity Eq. (6.0) yet.

Optimized Horn for Gramophone

[0535] FIG. 7a case (A) shows schematically a divergent horn 7a.A, submerged in a molecular fluid (for the sake of concretization, the molecular fluid is air) and exposed to a portion of sound 7a.A0 entering an open inlet 7a.A1 and outflowing from the open outlet 7a.A2 of the divergent horn 7a.A. The specific conveying motion of the air mass density is interpreted as composed of two complementary alternating movements of positive and negative changes of air mass density, wherein both alternating movements are in the same direction (that is the direction of sound propagation) and, when in open space or at the open inlet 7a.A1, with the M-velocity of 1 Mach. The specific conveying motion of the air mass density is subjected to influence within the divergent horn 7a.A. The cross-sectional area of the divergent horn 7a.A varies along the divergent horn 7a.A length, i.e. along a sagittal axis 7a.A5, in accordance with the condition of flow continuity Eq. (6.0) such that to provide substantially laminar motion of the positive and negative changes of air mass density within the divergent horn 7a.A due to the enhanced de Laval jet-effect applied to the moving positive and negative changes of air mass density, moving with the high M-velocity, higher than the specific M-velocity. The enhanced de Laval jet-effect, in particular, results in extra-acceleration of the laminar motion of the positive and negative changes of air mass density within the divergent horn 7a.A at the expense of the air heat understood in the wide sense including the concomitant turbulence inherently accompanying the sound. Thus, the portion of sound 7a.A0 becomes boosted due to the enhanced de Laval jet-effect.

[0536] In practice, sometimes, not optimized functioning of the divergent horn 7a.A occurs at least because of other portions 7a.A6 and 7a.A7 of ambient sound enter the divergent horn 7a.A through the sidewalls of the divergent horn 7a.A. To prevent the undesired reason, the divergent horn 7a.A is further supplied with a matrix TE device 7a.A4 covering the surface of the divergent horn 7a.A. The matrix TE device 7a.A4, when functioning like the multi-module thermoelectric device 5R.DEVICE comprising a matrix of a multiplicity of N ELEMENTAL DETECTORS OF SOUND 5R.02 which results in the zero 5R.4.OUTPUT as described hereinabove referring to FIG. 5r, is capable to isolate the entered portion 7a.A0 from the interfering portions 7a.A6 and 7a.A7.

[0537] It will be evident for a person, who has studied the present invention, that the ELEMENTAL SOURCE OF SOUND 5P.0A described hereinabove referring to FIG. 5P Case (A), can play the role of a source of the sound 7a.A0, and so the ELEMENTAL SOURCE OF SOUND 5P.0A supplied with the divergent horn 7a.A performs an efficiently functioning megaphone.

Phonendoscope and Sound Booster

[0538] FIG. 7a cases (B) and (C) are schematic illustrations of two-stage convergent-divergent nozzles 7a.B and 7a.C, destined for amplifying the intensity of an entering portion of sound 7a.B0 and 7a.C0, correspondingly. The enhanced phonendoscope 7a.B and sound booster 7a.C, both constructed according to the principles of the present invention, comprise common configurational features, and while the two-stage convergent-divergent nozzle 7a.B is configured to be used as an enhanced phonendoscope 7a.B, the two-stage convergent-divergent nozzle 7a.C is configured to have a corpus 7a.C1 ergonomically adapted to a human's ear canal, thereby, allowing to be used as a sound booster 7a.C ergonomically adapted to a human's ear 7a.EAR.

[0539] The mentioned common configurational features are related to optimized two-stage convergent-divergent tunnels 7a.B2 and 7a.C2. Correspondingly, there are common features elaborated according to the condition of flow continuity Eq. (6.0) as follows: [0540] open inlet 7a.B5 and 7a.C5 of the cross-sectional area A.sub.in, and [0541] open outlet 7a.B6 and 7a.C6 of the cross-sectional area A.sub.ou, [0542] shaped portions of varying cross-section: [0543] a convergent funnel 7a.B41 and 7a.C41, [0544] the first-stage narrow throat 7a.B42 and 7a.C42 having a local minimal cross-sectional area A.sub.th1, [0545] a widened cavity 7a.B43 and 7a.C43 having a local maximal cross-sectional area A.sub.ca, [0546] the second-stage narrow throat 7a.B44 and 7a.C44 having the local minimal cross-sectional area A.sub.th2, wherein A.sub.th2 at most equal to A.sub.th1, and [0547] divergent funnel 7a.B45 and 7a.C45.
Sound 7a.C0, when entering the open inlet 7a.C5, becomes subjected to the action of the optimized convergent-divergent tunnel 7a.C2 such that, [0548] first, when the sound 7a.C0 propagates through convergent funnel 7a.C41, the sound intensity becomes, [0549] on the one hand, decreased because the mass density change conveying with the velocity of sound becomes subjected to retarding due to the de Laval retarding effect applied to the mass density change moving with the high velocity, higher than the specific M-velocity, and [0550] on the other hand, increased due to: [0551] superposition of spatially distributed portions of sound becoming concentrated and joint in-phase, thereby, resulting in constructive interference, [0552] transformation of the internal heat energy of fluid into the acquired power of sound, as a manifestation of the Venturi effect, applied to longitudinal oscillation motion with the particle velocity, and [0553] suppression of concomitant turbulence, power of which, in the final analysis, becomes transformed into the acquired power of sound, as a phenomenon accompanying the Venturi effect applied to longitudinal oscillation motion with the particle velocity; [0554] second, the condition: A.sub.in/A.sub.th1≥1/M.sub.*, where M.sub.*=√{square root over ((γ−1)/γ)}, is satisfied and so, when the sound propagates through the first-stage narrow throat 7a.C42, the sound intensity is predetermined by the conveying velocity u.sub.convey and particle velocity u.sub.particle, wherein the local conveying M-velocity is of M.sub.* when crossing the narrowest cross-section within the first-stage narrow throat 7a.C42; [0555] third, the condition: A.sub.ca/A.sub.th1>1 is satisfied and so, when the sound propagates through widened cavity 7a.C43, the local conveying M-velocity becomes lower than the specific M-velocity M.sub.*, due to the de Laval retarding effect; [0556] fourth, the conditions: A.sub.ca/A.sub.th2≥1/M.sub.* and A.sub.th2/A.sub.th1≤1, both are satisfied and so, when the sound propagates through the second-stage narrow throat 7a.C44, the local conveying M-velocity reaches the specific M-velocity M.sub.*, due to the de Laval jet-effect; and [0557] fifth, the conditions: A.sub.ca/A.sub.th2≥1/M.sub.* and A.sub.ou/A.sub.th2≥1/M.sub.*, both are satisfied and so, when the sound propagates further through divergent funnel 7a.C45, the sound intensity becomes increased because the mass density change conveying with the varying velocity of sound becomes subjected to extra-acceleration due to the enhanced de Laval jet-effect, optimized to suppress turbulent component of the complicated movement of fluid when conveying the sound and applied to the mass density change moving with the high velocity, higher than the specific M-velocity; this effect of sound boosting is similar to that which occurs when using a classic gramophone supplied with an exponentially-divergent horn as described hereinabove in THE BACKGROUND OF THE INVENTION referring to prior art FIG. 1n, but now the divergent funnel configuration is optimized according to the condition of flow continuity Eq. (6.0).
In view of the foregoing description of the sub-paragraphs “Optimized Horn For Grammophone” referring to FIG. 7a case (A) and “Phonendoscope and Sound Booster” referring to FIG. 7a cases (B) and (C) in combination with the description of sub-paragraphs: “Sound as Complicated Movement in Molecular Fluid” referring to prior art FIG. 1n and “External Ear as Sound Booster” referring to prior art FIG. 1L, it becomes evident to a person who has studied the present patent application that, conceptually: [0558] The external ear 1L.0 (FIG. 1L) functions as the described passive sound booster 7a.C, but not optimized for suppression of concomitant turbulences according to the condition Eq. (6.0) yet; [0559] An optimized two-stage convergent-divergent nozzle, optimized for suppression of concomitant turbulences according to the condition of flow continuity Eq. (6.0), can be adapted to a diversity of applications as a wave-guiding and sound-amplifying nozzle for detectors or launchers of sound, for instance: [0560] the optimized two-stage convergent-divergent nozzle 7a.B can be utilized as a phonendoscope; and [0561] the optimized two-stage convergent-divergent nozzle 7a.C can be miniaturized to become adapted to the size of a human's ear canal and play a role of a passive sound booster utilized for amplifying the loudness of a portion of ambient sound; [0562] and [0563] An optimized divergent horn, optimized for widening a front of sound accompanied by suppression of concomitant turbulences according to the condition of flow continuity Eq. (6.0), can be scaled to play the role of an enhanced generalized gramophone utilized for boosting a sound launched by a source of acoustic waves.

[0564] It will be also evident for a person, who has studied the present invention, that each of the two-stage convergent-divergent nozzles 7a.B and 7a.C, when supplied with the two-stage sound amplifier 5S.DEVICE described hereinabove referring to FIG. 5, can play the role of an efficiently functioning hearing aid.

Compressor supplied by Convergent-Divergent Jet-Nozzle

[0565] FIG. 7b, having two parts: Case (A) and Case (B), is a schematic illustration of a pressure-transformer 710.P and a heat-transformer 710.H, correspondingly, both constructed according to the principles of the present invention, to accelerate a compressed and heated air portion.

[0566] In pressure-transformer 710.P, the optimized convergent-divergent jet-nozzle 710 with the critical condition point 718 comprises a reservoir 712 where an air portion 711 is compressed and thereby heated due to a piston 714. As it was described hereinabove referring to FIG. 7, to trigger the enhanced de Laval jet-effect, one needs either to compress air portion 711 up to the static pressure P.sub.0=1.893×P.sub.a, where P.sub.a is the ambient pressure (for instance, P.sub.a=1 bar), or, alternatively, to heat the air portion 711 up to the absolute temperature T.sub.0=1.2×T.sub.a, where T.sub.a is the ambient temperature (for instance, T.sub.a=298 K), wherein the static pressure P.sub.0 and increased temperature T.sub.0 are interrelated. In this case, if the divergent portion 710 of the optimized de Laval nozzle has the outlet cross-sectional area wider than the cross-sectional area at the critical condition point 718 by the factor 1/M.sub.*=√{square root over (γ/(γ−1))}, the M-velocity of the outflowing stream 713 is about 1 Mach. To compress air portion 711 up to pressure P.sub.0=1.893 bar one needs to consume the energy E.sub.0 estimated as (P.sub.0−P.sub.a)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≈0.9×10.sup.5 J=90 kJ. The volume V.sub.0 is composed of approximately n≈(P.sub.0/P.sub.a)×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.a and the temperature decreases from T.sub.0 to T.sub.a. Again, consider the air portion 711 acceleration 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, i.e. such that 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, where T.sub.e is the absolute temperature of the cold outflowing stream 713 wherein the temperature difference (T.sub.0−T.sub.e)=0.412T.sub.0 is estimated as 123 C. 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≈9,761,674J=9,762 kJ.

[0567] This estimation shows that, taking into account a 15% net-efficiency of an engine pushing the piston 714, the triggered acquired kinetic energy K may exceed the triggering consumed energy E.sub.0 at least at subsonic velocities by the factor of about 16 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 a thermoelectric generator and/or as an effective condenser of vapor to water.

[0568] In heat-transformer 710.H, the optimized convergent-divergent jet-nozzle 710.B, optionally, unbrokenly covered with a multiplicity of thermoelectric devices 717.B similar to the surface matrix 6A.MATRIX of densely-arranged elemental thermoelectric devices 6A.TED described hereinabove referring to FIG. 6a, has the outlet cross-sectional area wider than the cross-sectional area at the critical condition point 718.B by the factor 1/M.sub.*=√{square root over (γ/(γ−1))} and supplied with a reservoir 712.B, a wall of which is covered with another multiplicity of thermoelectric devices 714.B and has a multiplicity of relatively long and narrow through-hole pipes 715.B. Shape of the through-hole pipes 715.B is not optimized for a laminar motion of flow neither if entering the reservoir 712.B nor if outflowing back to ambient space.

[0569] Inner air portions 711.B and outer air portions 716.B, both are subjected to the functioning of the multiplicity of thermoelectric devices 714.B such that, on the one hand, the inner air portions 711.B are heated and thereby compressed and, on the other hand, the outer air portions 716.B are cooled and thereby thickened. When the absolute temperature T.sub.0 of the inner portions 711.B is kept equal 1.2×T.sub.a [i.e. T.sub.0=357.6K, i.e. ΔT=(T.sub.0−T.sub.a)=59.6 C that, normally, is reachable by a thermoelectric device], the condition for triggering the enhanced de Laval jet-effect becomes satisfied. The optional covering with the multiplicity of thermoelectric devices 717.B is for controlling the temperature distribution dependent on the velocity of the inner portions 711.B, which (the velocity) in turn, is determined by the functioning of the multiplicity of thermoelectric devices 714.B; the controlling is to provide laminarity of flow 719.B within the optimized convergent-divergent jet-nozzle 710.B. Points 718.B symbolize that the thermoelectric devices 717.B cover the optimized convergent-divergent jet-nozzle 710.B unbrokenly. The asymmetry of conditions that, on the one hand, the temperature distribution along the relatively long pipes 715.B is not optimized for a laminar motion of the flow, and on the other hand, the tunnel 710.B is optimized for a laminar motion of the flow, causes a tendency of the inner air portions 711.B to move directionally through the optimized convergent-divergent jet-nozzle 710.B. As a result, the reservoir 712.B is permanently filled with the fresh outer portions 716.B via the through-hole pipes 715.B such that the velocity of the outflowing stream 713.B is almost as the speed of sound. Optionally, the pipes 715.B can be fulfilled as valvular conduits (Tesla valves) to increase the efficacy of the jet-nozzle 710.B.

[0570] Again, 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, where T.sub.e is the absolute temperature of the cold outflowing stream 713.B wherein the temperature difference (T.sub.0−T.sub.e)=0.412T.sub.0 is estimated as 123 C. 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≈9,761,674J=9,762 kJ.

Taking into account a 15% net-efficiency of the multiplicity of the thermoelectric device, the triggered acquired kinetic energy K may exceed the triggering consumed energy E.sub.0 at least at subsonic velocities by the factor of about 16 times. As the flow 719.B within the optimized convergent-divergent jet-nozzle 710.B becomes colder than the ambient fluid, the multiplicity of thermoelectric devices 717.B can be also used for harvesting of electricity.

[0571] In view of the foregoing description referring to FIG. 7b Case (B), it will be evident to a person skilled in the art that, instead of Peltier elements (thermoelectric devices 714.B), any kind of electric heater (i.e. a thermoelectric device in the broad sense) can be used to increase the temperature of the inner air portions 711.B, because the inertness of temperature difference controlling is not critical for a steady-established and relatively slow intake of air portions 711.B.

Flying Capsule as Dragging-Jet Engine

[0572] 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 an outer airfoil side 729 covered with a surface matrix thermoelectric device 729.TED and inner walls, which are formed by another surface matrix thermoelectric device 722.TED, in turn, forming a through-hole corridor having: [0573] an inner converging reservoir 721 as a dragging compressor having an open inlet 725 exposed to ambient wind 724, and further [0574] 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.

[0575] The velocity of ambient air 724 relative to capsule 720 is u.sub.a which is substantially lower than the critical condition velocity u, corresponding to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}. The wind portion 727 enters the inner converging reservoir 721 with a 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 enhanced de Laval jet-effect is expected in the divergent exhaust tailpipe having outlet 726, where the velocity of outflowing jetstream 723 reaches a value u.sub.723 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 and forcibly established temperature distribution along the inner walls using the surface matrix thermoelectric device 722.TED, both provide that the value u.sub.723 is lower than the speed of sound u.sub.sound. Outflowing jetstream 723 brings the kinetic power acquired at the expense of the flow's 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.

[0576] 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 both: forcibly established temperature distribution using the surface matrix thermoelectric device 729.TED and 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 the 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 the condition of flow continuity Eq. (6.0). On the other hand, at outlet 726, the velocity of inner sub-portion 723 is of value U.sub.723 higher than the critical condition velocity u.sub.*. According to the condition of flow continuity Eq. (6.0), 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 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 outflowing 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 outflowing divergent portion 735 has the M-velocity lower than the specific M-velocity M.sub.*.

[0577] In view of the foregoing description referring to FIG. 7c, it will be evident to a person skilled in the art that: [0578] The shape of tunnel 722 and the forcibly established temperature distribution along the inner walls using the surface matrix thermoelectric device 722.TED, both can be adapted to the velocity u.sub.a of ambient air 724 and optimized to provide that the velocity value u.sub.723 of outflowing 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 and forcibly established temperature distribution along the inner walls using the surface matrix thermoelectric device 729.TED, both can be optimized to provide that outflowing divergent portion 735 has increasing M-velocity reaching values higher than the specific M-velocity M.sub.*; [0579] Supplying a flying vehicle or helicopter's propeller blades by nozzles similar to capsule 720 operating as a 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, strongly according to the Energy Conservation Law. Furthermore, looking ahead referring to FIGS. 9d, 9e, and 9f described hereinbelow, point out that an even number of such jet-boosters, attached to the even number of blades of a helicopter's propeller, result in stabilization of the effective velocities of incoming and outflowing jetstreams associated with the jet-boosters. The predictably equalized velocities enable easier controllable lift-forces when the helicopter is flying speedily; [0580] The described airfoil capsule can be stationarily exposed to oncoming wind (either natural or artificial) and thereby become applicable to efficient harvesting of electricity providing a positive net-efficiency; and [0581] 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 outflowing 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 a thermoelectric generator, and/or vapor-into-water condenser.

[0582] 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. Similar to the flying capsule 720 illustrated hereinbefore referring to FIG. 7c, inner and outer walls 748 and 749 of capsule 740's tunnel and outer shell are supplied with forcedly controllable surface matrix thermoelectric devices 748.TED and 749.TED, correspondingly. 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 referring to FIG. 6c. 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 M.sub.743, 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 the condition of flow continuity Eq. (6.0), 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, and 6c. 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 outflowing jetstream 747 with a high M-velocity, higher than the de Laval high M-velocity of oncoming fast flow 743.

[0583] In view of the foregoing description referring to FIGS. 7c and 7d, it will be evident for a person skilled in the art that one can use the surface matrix thermoelectric devices to provide for at least one of: [0584] Adapting to the de Laval high M-velocity M.sub.743 of the oncoming fast flow 743 and controlling the laminarity of both: the flow 473 moving within the specifically shaped two-stage inner tunnel and outer portions of the ambient-adjacent flow; and [0585] Harvesting electricity from originated temperature differences.

Modified Symmetrical Wing

[0586] FIG. 8, a schematic illustration of a symmetrical wing 8.00 supplied with a multi-layer TE device 8.20, is composed of three sub-drawings: [0587] FIG. 8 (A) is a schematic drawing of a sectional profile of a modified symmetrical wing 8.00 in a sagittal plane (X, Z) in a system of coordinates (X, Y, Z); [0588] FIG. 8 (B) is a profile of temperature difference function ΔT(x) between two opposite surfaces: upper-side 8.01 and lower-side 8.02 along the X-axis in a system of coordinates (X, ΔT); and [0589] FIG. 8 (C) is a profile of temperature difference function ΔT(z) between two opposite butt-ends: anterior and tail, along the Z-axis in a system of coordinates (ΔT, Z).

[0590] The modified wing 8.00, mirror-symmetrical relative to the horizontal plane (X, Y), having a cross-sectional thickness 8.AZ, is oriented to meet the oncoming fluid flow 8.10 at the zero attack angle. The oncoming fluid flow 8.10, when flowing around the modified symmetrical wing 8.00, becomes divided into two portions: [0591] upper-side 8.11, forming the upper-side boundary layer 8.31 moving nearby the upper-side surface 8.01 and having thickness 8.41; and [0592] lower-side 8.12, forming the upper-side boundary layer 8.32 moving nearby the lower-side surface 8.02 and having thickness 8.42;
each of which is subjected to the action of the Coanda-effect. If the upper-side 8.01 and lower-side 8.02 surfaces of the modified symmetrical wing 8.00 are made from the same material and have the same temperature, the two portions: upper-side 8.11 and lower-side 8.12, of fluid flow, both are subjected to the mirror-symmetrically acting Coanda-effect such that the lift-force is zero and only the Archimedes' upward-vectored force 8.LIFT acts on the modified symmetrical wing 800 against the downward attracting gravitational force. Normally, the effective mass density of the modified symmetrical wing 800 is much greater than the mass density of the natural air, and if the ambient fluid is the natural air, then the Archimedes' upward-vectored force is much weaker than the downward attracting gravitational force. Speaking strictly, the two boundary layers 8.31 and 8.32 differ in thermodynamic parameters: the static pressure, mass density, and absolute temperature, as the boundary layers 8.31 and 8.32, both characterized by the mass density and subjected to gravitational downward attraction, occupy spaces differing in height above the world Oceanus level. The seemingly-insignificant difference in the static pressures is a reason for the Archimedes' upward-vectored force.

[0593] The modified symmetrical wing 800 is modified by that the upper-side 8.01 and lower-side 8.02 surfaces are mutually-contacted through the multi-layer TE device 8.20, which is similar to the multi-layer TE multi-module device 1t.0 comprising a matrix of TE elements aggregated in layers one above another multi-stage repeatedly as described hereinabove referring to prior art FIG. 1t The multi-layer TE device 8.20 comprises: [0594] the upper-side layer composed of unbrokenly arranged anterior TE devices 821, withers TE devices 8.23, and tail TE devices 8.25, all having an upper side forming the upper-side surface 8.01 of the modified symmetrical wing 8.00, and [0595] the lower-side layer composed of unbrokenly arranged anterior TE devices 8.22, withers TE devices 824, and tail TE devices 8.26, all having a lower side forming the lower-side surface 8.02 of the modified symmetrical wing 8.00,
wherein points 8.27 and 8.28 symbolize that TE devices are arranged unbrokenly.

[0596] The multi-layer TE device 8.20, when controlled by a controller, provides for an additional temperature difference 8.ΔT(x) (additional to the seemingly-insignificant temperature difference) between the upper-side 8.01 and lower-side 8.02 surfaces along the X-axis.

[0597] The profile of the modified symmetrical wing 8.00 is airfoil in a certain sense only. When the ambient velocity is in a certain range of velocities, the stalling effect, accompanied by broken or jumping all: the headway velocity, the static pressure, the absolute temperature, and the mass density, occurs nearby the separation point 1G.46 resulting in reducing lift-force drastically, as described hereinabove in the subparagraph: “Broken Boundary Layer” referring to FIG. 1g Scheme (E).

[0598] The inventor points out that all parameters: the headway velocity, the static pressure, the absolute temperature, and the mass density, are interrelated according to laws of gas state and laws of aerodynamics, and so controlling of at least one of the parameters allows to control all the other parameters. In particular, to suppress the uncontrolled stalling effect, the use of the multi-layer TE device 8.20 controlled by a controller allows for providing a forcibly established specific temperature distribution along the upper-side 8.01 and lower-side 8.02 contours of the modified symmetrical wing 8.00 profile. The forcibly established specific temperature distribution along the upper-side 8.01 and lower-side 8.02 contours is such to provide the mentioned thermodynamic conditions for laminar flowing in the boundary layers 8.31 and 8.32, correspondingly, each of which becomes an optimized convergent-divergent nozzle, completely optimized on one of the mentioned criteria either: [0599] smoothing of the flowing fluid M-velocity, or [0600] smoothing of the flowing fluid static pressure, or [0601] smoothing of the flowing fluid absolute temperature, or [0602] smoothing of the flowing fluid mass density,
as described hereinabove in the subparagraph “Convergent-Divergent Jet-Nozzle” referring to FIG. 6a. Thus, it is preferred to use a specifically distributed additional temperature difference 8.ΔT(x), distributed along the contours 8.01 and 8.02. An exemplary distribution of the additional temperature difference 8.ΔT(x) is optimized to provide laminar motions of portions 8.11 and 8.12 accompanied by gradual changes in M-velocities dependent on the cross-sectional area of the boundary layers 8.31 and 8.32, correspondingly, according to the condition of flow continuity Eq. (6.0), adapted to the M-velocity of oncoming flow 8.10 equal to 0.35 Mach and effective thicknesses 8.41 and 8.42, both equal to 3.7 cm. The specifically distributed additional temperature difference 8.ΔT(x), having a zone downstream behind the TE devices 8.25 and 8.26 where the temperature differences 8.T2 are reversed in sign, is such that, downstream behind the sharp butt-end 8.03 of the modified symmetrical wing 8.00, the velocities of the upper-side 8.11 and lower-side 8.12 portions gradually become the same and the temperatures of both upper-side 8.11 and lower-side 8.12 portions become gradually reverted to the temperature of the ambient fluid. This condition is necessary to prevent or at least to suppress turbulence downstream behind the sharp butt-end 8.03 thereby making the modified symmetrical wing 8.00 actually-airfoil.

[0603] Considering an action of the multi-layer TE device 8.20 making the upper-side surface 8.01 colder than the lower-side surface 8.02, when fresh portions of fluid are suddenly transformed into the upper-side and lower-side boundary layers, the additional effective temperature difference 8.ΔT(eff) equal to ΔT causes suddenly originated effective temperature differences between fluid portions, i.e.: [0604] ΔT.sub.1 between the upper-side portion of the ambient fluid and a tiny portion within the refreshed upper-side boundary layer 8.31, [0605] ΔT.sub.2 between a tiny portion within the refreshed upper-side boundary layer 8.31 and a tiny portion within the refreshed lower-side boundary layer 8.32, [0606] ΔT.sub.3 between a tiny portion within the refreshed lower-side boundary layer 8.32 and the refreshed lower-side portion of the ambient fluid,
wherein the condition: ΔT.sub.2=−(ΔT.sub.1+ΔT.sub.3) says that the ambient fluid outside the boundary layers remains in the normal thermodynamic conditions. There are extremely low velocities of airflow in close proximity above the upper-side solid surface 8.01 and under the lower-side solid surface 8.02 as described hereinabove in the subparagraph: “Boundary-layer” referring to FIG. 1g Graph (D). Hence, the condition ΔT.sub.2≤ΔT (again, ΔT is the additional effective temperature difference 8.ΔT(eff) between the upper-side and lower-side surfaces: 8.01 and 8.02) is satisfied also when the wing 8.00 moves. When the refreshed boundary layers are relatively thin and well-aligned with the airfoil surfaces, the approximation ΔT.sub.2≅ΔT becomes justified. The higher the ambient velocity, the thinner the refreshed boundary layers, and the more appropriate the interrelation ΔT.sub.2≅ΔT.sub.* Further, for concretization, the relatively thin and well-aligned boundary layers flowing with high-subsonic velocities are assumed. Considering fresh incoming portions of the boundary layers, the suddenly originated additional effective temperature differences ΔT.sub.1, ΔT.sub.2, and ΔT.sub.3 are interrelated with the suddenly originated additional effective static pressure differences, additional to the seemingly-insignificant static pressure difference associated with Archimedes' upward-vectored force. Namely, the suddenly originated ΔT.sub.1, ΔT.sub.2, and ΔT.sub.3 are interrelated with the suddenly originated additional effective static pressure differences of: [0607] ΔP.sub.1 between the upper-side portion of the ambient fluid and a tiny portion within the refreshed upper-side boundary layer 8.31, [0608] ΔP.sub.2 between a tiny portion within the refreshed upper-side boundary layer 8.31 and a tiny portion within the refreshed lower-side boundary layer 8.32, [0609] ΔP.sub.3 between a tiny portion within the refreshed lower-side boundary layer 8.32 and the refreshed lower-side portion of the ambient fluid,
correspondingly. The resulting suddenly originated negative additional effective pressure difference ΔP.sub.2 interrelates with the suddenly originated positive additional effective pressure differences: ΔP.sub.1 and ΔP.sub.3, wherein: [0610] the suddenly originated positive additional effective pressure difference ΔP.sub.1 results in downward pulling-in the upper-side portion of the ambient fluid and upward pulling-in the modified symmetrical wing 8.00 into the refreshed upper-side boundary layer 8.31, and [0611] the suddenly originated positive additional effective pressure difference ΔP.sub.3 results in downward pushing-off the lower-side portion of the ambient fluid and upward pushing-off the modified wing symmetrical 8.00 away from the refreshed lower-side boundary layer 8.32,
thereby, both contributing to the upward-vectored force 8.LIFT applied to the modified symmetrical wing 8.00 in unison, wherein the condition: ΔP.sub.2=−(ΔP.sub.1+ΔP.sub.3) says that the ambient fluid outside the boundary layers remains in the normal thermodynamic conditions. Thus, the suddenly originated additional positive effective pressure difference (−ΔP.sub.2)=(ΔP.sub.1+ΔP.sub.3) works for both: [0612] downward shifting the upper-side and lower-side portions of the ambient fluid, and [0613] a positive contribution ΔF.sub.LIFT to the upward-vectored force 8.LIFT,
in the same extent, i.e. not more than half the sum (ΔP.sub.1+ΔP.sub.3) contributes to the lift. Moreover, as the contribution to the lift works if the additional effective static pressure differences are originated between two fresh portions of air just suddenly, a velocity-dependent suddenness factor C.sub.S determines the value of the positive contribution ΔF.sub.LIFT to the upward-vectored force 8.LIFT. Namely, as the interaction between, on the one hand, the wing and, on the other hand, the refreshed and suddenly heated or cooled boundary layers is relevant only, then, when the relatively thin boundary layers (the thickness of which is velocity-dependent) are strictly-aligned to the relatively big airfoil surfaces of the modified symmetrical wing 8.00, the velocity-dependent suddenness factor C.sub.S tends to 1 (C.sub.S.fwdarw.1), and, the slower-refreshed and so thicker the boundary layer and the weaker the alignment, the smaller the velocity-dependent suddenness factor C.sub.S. Assuming an airfoil corpus, a simplified approximation for the velocity-dependent suddenness factor C.sub.S defined hereinabove by the equitation Eq. (1.1j) is further specified for higher M-velocities by the expression:

[00022] $\begin{matrix} C_{S} = {\begin{matrix} M / M_{*}, & M \leq M_{*} \\ \exp (1 - M / M_{*}), & M > M_{*} \end{matrix}, & Eq . (8.0 a) \end{matrix}$

where M is M-velocity and M.sub.* is the specific M-velocity. The approximation Eq. (8.0a) makes physical sense: the greater the difference |1−M/M.sub.*|, the lower the suddenness factor, which is manifested as a thicker boundary layer. Thus, the positive contribution ΔF.sub.LIFT is defined as:

ΔF.sub.LIFT=½×C.sub.S×A.sub.(X,Y)×(−ΔP.sub.2), Eq. (8.0b)

where A.sub.(X,Y) is the area of a projection of the upper-side surface 8.01 (or the lower-side surface 8.02) of the modified symmetrical wing 8.00 in a horizontal plane (X, Y). As the high-subsonic velocity range is assumed, the approximation C.sub.S=1 is used for the estimation of the concept's practicality for industrial use [For comparison, in the case of wings waving by a pigeon to result in the effect of the bird taking-off dominantly-vertically (the case is highlighted hereinabove in the subparagraph “Flying Bird” referring to FIG. 1i), the suddenness factor C.sub.S is estimated as about 0.01 that gives ΔF.sub.LIFT of approximately 3.5N obtained by the waving that explains the effect of the bird taking off dominantly-vertically so efficiently]. To evaluate the concept's practicality for industrial use, an exemplary positive contribution ΔF.sub.LIFT to the upward-vectored force 8.LIFT is estimated referring to the specifically distributed additional temperature difference 8.ΔT(x) considering: [0614] the normal ambient air conditions: T≈300K, P≈100,000 Pa, and γ=7/5; [0615] the wing 8.00 having a chord of 2 m and a span of 10 m; i.e. A.sub.(X,Y)=20 m.sup.2; and [0616] the normally reachable value of the additional temperature difference 8.T1 using TE devices is −75 C, and taking into account that it is preferred to use the specifically distributed additional temperature difference 8.ΔT(x), distributed on the upper-side 8.01 and lower-side 8.02 surfaces along the X-axis, the suddenly originated effective difference of ΔT.sub.2=ΔT=−30 C is taken for the estimation, noting that ΔT.sub.2 is interrelated with the suddenly originated effective additional static pressure difference ΔP.sub.2 according to equation Eq. (1.1b) described hereinabove in the subparagraph “Lift-Force Mechanism” referring to FIG. 1g.
Thereby, the values are quantified as follows: C.sub.S=1, the ratio (−ΔT.sub.2)/T≈0.1, the ratio (−ΔP.sub.2)/P≈0.1×(7/5)/(2/5)=0.35, the suddenly originated additional static pressure difference is (−ΔP.sub.2)=(ΔP.sub.1+ΔP.sub.3)≈0.35×10.sup.5 Pa, and the contribution ΔF.sub.LIFT 8.LIFT to the upward-vectored force is

ΔF.sub.LIFT=½×C.sub.S×A.sub.(X,Y)×(−ΔP.sub.2)≈0.35×10.sup.6N Eq. (8.0c)

that is sufficient to support a mass of 35 ton fast-moving horizontally in the air.

[0617] In view of the foregoing description referring to FIGS. 8 (A) and (B), it will evident for a person skilled in the art that the modified symmetrical wing 8.00 has advantages as follows: [0618] it becomes relevant to use an increased upward-vectored force, increased by the contribution ΔF.sub.LIFT, to contribute to the lift-force; [0619] it is possible to use the zero attack angle only or at least dominantly but not to use flaps to control lift-force; [0620] it becomes possible to control flow laminarity within the upper-side and lower-side boundary layers; [0621] it becomes solved the problem of arising a negative lift-force at M-velocities higher than the specific M-velocity; and [0622] it becomes possible to imitate an actually-airfoil wing by suppression turbulence downstream behind the modified symmetrical wing.
Further, the controlled multi-layer TE device 8.20 allows for the controllable creation of an additionally distributed temperature difference 8.ΔT(z) between the anterior and tail butt-ends of the modified symmetrical wing 800. For the sake of concretization, the shown additional distributed temperature difference 8.ΔT(z) is negative such that the additionally distributed temperature difference 8.ΔT(z) providing the negative effective temperature difference ΔT.sub.FORE-TAIL between the anterior and tail butt-ends. Analogously and in contrast to the origination of the positive contribution to the lift-force 8.LIFT by the added upward-vectored force ΔF.sub.LIFT, a contribution to the thrust 8.THRUST by the added positive thrust ΔF.sub.THRUST is provided due to the added negative effective temperature difference ΔT.sub.HEAD-TAIL interrelated with the added negative effective static pressure difference ΔP.sub.HEAD-TAIL. Namely, analogously to the specification of the force ΔF.sub.LIFT, the force ΔF.sub.THRUST is specified as:

ΔF.sub.THRUST=−½×C.sub.u×ΔP.sub.HEAD-TAIL×A.sub.(Y,Z) Eq. (8.0d),

where A.sub.(Y,Z) is the cross-sectional area in a frontal plane (Y, Z). To estimate the practicality of the concept, an exemplary positive contribution ΔF.sub.THRUST to thrust 8.THRUST is estimated referring to the added negative effective temperature difference ΔT.sub.FORE-TAIL considering: [0623] the value of cross-sectional thickness 8.ΔZ of the modified symmetrical wing 8.00 equal to 0.2 m and a span of 10 m; i.e. A.sub.(Y,Z)=2 m.sup.2; and [0624] the value of the negative effective temperature difference ΔT.sub.HEAD-TAIL using TE devices of −60 C, i.e. the ratio (−ΔT.sub.HEAD-TAIL)/T≈0.2; so, referring to the equation Eq. (1.1b) described hereinabove in the subparagraph “Sound as Complicated Movement in Molecular Fluid” prefacing the reference to FIG. 1n, the ratio (−ΔP.sub.HEAD-TAIL)/P≈0.7, and (−ΔP.sub.HEAD-TAIL)≈0.7×10.sup.5 Pa.
Thereby, the force ΔF.sub.THRUST is estimated as (½)×(0.7×10.sup.5 Pa)×(2 m.sup.2)=0.7×10.sup.5 N that is sufficient to overcome a velocity-dependent drag in the air when moving with the headway velocity u.sub.0 of the high-subsonic velocity range, that can be confirmed referring to the condition derived from the well-known drag and skin-friction equation as follows:

U.sub.0={|ΔF.sub.THRUST|/[0.5×ρ.sub.AIR×(C.sub.d×A.sub.(Y,Z)+C.sub.f×A.sub.(X,Y))]} Eq. (8.0e),

where: A.sub.(Y,Z)=2 m.sup.2, A.sub.(X,Y)=20 m.sup.2, [0625] C.sub.f is the skin-friction coefficient, normally, given as about 0.045 for an airfoil wing, [0626] C.sub.d is the drag coefficient, normally, given as about 0.5 for a frontal convexly-rounded configuration of an actually-airfoil wing, and [0627] ρ.sub.AIR is the mass density of the air, normally, given as about 1.18 kg/m.sup.3, [0628] i.e. u.sub.0≈250 m/sec.

[0629] In view of the foregoing description of the subparagraph “Modified Symmetrical Wing” referring to FIG. 8, it becomes evident for a commonly educated person that, using the surface matrix thermoelectric devices, a spatial function of temperature differences ΔT(x,z) within boundary layers can be enforced to provide for temperature asymmetry of a geometrically symmetrical wing to control lift-force and thrust, and, in particular, flying capsules 720 and 740 described hereinabove in the subparagraph “Flying Capsule as Dragging-Jet Engine” referring to FIGS. 7c and 7d, both can have an optimized thrust and controlled lift-force.

Shaped Wing as a Convergent-Divergent Jet-Nozzle

[0630] FIG. 8a is a schematic visualization 800 of an oncoming wind portion 820, without loss of generality, moving horizontally and flowing around actually-airfoil biconvex wing 810, supplied with a multi-layer TE device 8a.TED. Oncoming wind portion 820 comprises airflow sub-portions 821, 822, 823, and 824 flowing around actually-airfoil biconvex wing 810, having a side-view sectional profile, constructed according to the principles of the present invention. The side-view sectional profile determines a sagittal axis 820.0. The upper side of actually-airfoil biconvex wing 810 comprises: [0631] (a) a forward part meeting upper-side sub-portion 822 having imaginary cross-section 831; [0632] (b) a withers 810a 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 [0633] (c) a rearward part, attracting and, thereby, redirecting the mass-center of the upper-side sliding sub-portion 822 backward-downward, where sliding sub-portion 822 has imaginary widened cross-section 833.
The upper and lower sides of the actually-airfoil biconvex wing 810, each having a convexity: 810a and 810b, correspondingly, join together forming a sharp trailing end 810c.

[0634] 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 biconvex 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 biconvex wing 810, keep substantially straight trajectories aligned with imaginary horizontal lines 811 and 812 (collinear with the sagittal axis 820.0) correspondingly above and under actually-airfoil wing 810. Actually-airfoil biconvex 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), where a and a.sub.w are the van der Waals parameters characterizing the fluid and attraction between the fluid and an adjacent wall, correspondingly, and δa is the van der Waals parameter characterizing the partial deep-stagnation pressure-a δP.sub.a. Imaginary lines 811 and 812 can be considered as imaginary walls, thereby, together with the airfoil-profile forming imaginary nozzles. The upper-side imaginary nozzle comprises imaginary cross-sections 831, 832, and 833, and the lower-side 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-side 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-side imaginary nozzle has a converging shape.

[0635] The orientation of the sharp trailing end 810c collinear with the sagittal axis 820.0 predetermines the direction of motion tendency of the outflowing sub-portions 822 and 823, which are going off from the sharp trailing end and joining downstream behind the cross-sections 833 and 835, correspondingly. For the purposes of the present invention, an angle between the sagittal axis 820.0 collinear with the direction of motion tendency of the lower-side outflowing sub-portion 823 and the horizontal direction defines an angle of attack (called also an attack angle). The definition of the attack angle is in conformance with the definition of the attack angle specified hereinabove in the subparagraph “Airfoil Wing (definition of attack angle)” of THE BACKGROUND OF THE INVENTION for a classic wing associated with a fuselage of airplane. Here is the zero attack angle in the shown schematic visualization 800. The zero attack angle provides for minimized impact by the oncoming flow and a generation of the lift-force due to the Coanda-effect only or at least dominantly.

[0636] Consider a case, when actually-airfoil biconvex wing 810 flies with a certain de Laval low M-velocity M.sub.810 that is lower than the specific M-velocity M.sub.*≈0.5345 Mach≈664 km/h, but such that sliding sub-portion 822, moving through the upper-side 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-side imaginary convergent-divergent jet-nozzle. This is accompanied by the static pressure decrease and extra-decrease, as described hereinabove with the reference to FIG. 6a (B) Graph, and thereby results in the lift-effect, becoming stronger. The narrowest cross-section 832 linear size, i.e. thickness δ of a boundary layer, dependent on both a so-called “characteristic size” L.sub.* and the so-called Reynolds Number Re, can be estimated using, for example, approximation by Prandtl: δ=0.37×L.sub.*/Re.sup.0.2, where L.sub.* has the sense of a chord of an airfoil wing. As well, the thickness δ of the boundary layer can be specified experimentally for a kind of body corpus. 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, interpreting the narrowest cross-section 832's linear size as the thickness of the boundary layer, one can apply the condition of flow continuity Eq. (6.0) to design an improved profile of the wing.

[0637] 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. 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.

[0638] Further, it will be evident to a person skilled in the art that considering the case, when actually-airfoil biconvex wing 810 flying with a certain Venturi M-velocity M.sub.810, [0639] which (the Venturi M-velocity M.sub.810) is lower than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach≈664 km/h and such that, when sliding sub-portion 822 moves through the upper-side imaginary nozzle and passes through the narrowest cross-section 832, the maximally accelerated M-velocity remains lower than the specific M-velocity M.sub.*,
the condition of flow continuity Eq. (6.0) allows designing an improved profile of the wing optimized to meet flow, oncoming with the Venturi M-velocity M.sub.810. While a gradual change in static pressure within boundary layers adjacent to the upper-side and lower-side surfaces of the actually-airfoil biconvex wing 810 is the primary condition for the suppression of undesired turbulences nearby the wing surfaces, one of the primary criteria of the optimization is also to provide minimized differences between velocity-vectors and static pressures of the outflowing sub-portions 822 and 823, as the primary condition for suppression of undesired turbulences downstream behind the sharp trailing end 810c. While the curvatures of the upper-side and lower-side surfaces should provide gradual changes of the static pressures and M-velocities, the sharpness of the sharp trailing end 810c should provide the dominantly horizontal direction of motion tendency of both outflowing sub-portions 822 and 823.

[0640] Thus, a method for a wing profile design, based on the condition of flow continuity Eq. (6.0) 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 Coanda-jet-effect accompanied by enhanced at least one of the Venturi effect and de Laval jet-effect occurring above and under the wing. The inventor notes that the profile of the actually-airfoil biconvex wing 810, designed and optimized using the condition of flow continuity Eq. (6.0), has a shape similar to a shape of a birdwing rather than to the shape of the classic wing of the airplane.

[0641] The actually-airfoil biconvex wing 810, while designed and optimized using the condition of flow continuity Eq. (6.0) applied to the overall geometrical configuration only, is actually-airfoil in a certain sense when considering the mentioned certain M-velocity M.sub.810. To provide optimized conditions for a wide range of velocities, the actually-airfoil biconvex wing 810, is further supplied with the multi-layer TE device 8a.TED built-in between the upper-side and lower-side surfaces of the actually-airfoil biconvex wing 810. The multi-layer TE device 8a.TED comprises: [0642] an upper side forming the upper-side surface of the actually-airfoil biconvex wing 810, and [0643] a lower side forming the lower-side surface of the actually-airfoil biconvex wing 810.

[0644] The multi-layer TE device 8a.TED, when controlled by a controller, provides for additional forcibly established temperature difference, additional to the temperature difference between the upper-side and lower-side surfaces along the sagittal axis 820.0 determined by the Coanda-effect accompanied by at least one of the Venturi effect and the de Laval effect. The forcibly established temperature difference (ΔT.sub.0(x)+ΔT(x)) distributed along the sagittal axis 820.0, where: [0645] ΔT.sub.0(x) is the distributed original temperature difference between the upper-side and lower-side boundary layers specified when designing the overall geometrical configuration of the actually-airfoil biconvex wing 810 considering the mentioned certain M-velocity M.sub.810 and the derivative distribution M.sub.810(x) along the sagittal axis 820.0, and [0646] ΔT(x) is the additional forcibly established distribution of the temperature difference, provides for adaptation of the overall shape of the actually-airfoil biconvex wing 810 to an arbitrary velocity u.sub.8a of the oncoming wind portion 820. For this purpose, the forcibly established distribution of the temperature difference (ΔT.sub.0(x)+ΔT(x)) is defined as:

[00023] $(Δ T_{0} (x) + Δ T (x)) = \frac{1}{γ R} \times {[\frac{u_{8 a}}{M_{810} (x)}]}^{2} .$

The Coanda-Effect Operation Providing an Imaginary Convergent-Divergent Nozzle

[0647] 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: [0648] a forward part meeting oncoming flow portion 851; [0649] 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 [0650] a rearward part.

[0651] 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-portions 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.

[0652] 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 outflowing convergent-divergent jetstream.

[0653] As the shape of the imaginary convergent-divergent tunnel comprising streamlines 843-844 and cross-sections 863, 864, and 865 is a derivation of the Coanda-effect operation nearby the solid surfaces of the airfoil body 840, the airfoil body 840 is supplied with a matrix TE device (which is not shown here), built-in within the airfoil body 840's corpus and in close proximity under the solid surfaces to control the surface temperature and thereby to control the Coanda-effect and laminarity of the streamlines 842-843-844.

Jet-Booster Based on the Venturi Effect

[0654] 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: [0655] M.sub.861<M.sub.868<M.sub.*, [0656] M.sub.863<M.sub.868<M.sub.*, [0657] M.sub.863<M.sub.864<M.sub.*, [0658] M.sub.861<M.sub.864<M.sub.*, and [0659] M.sub.865<M.sub.864<M.sub.*.

[0660] Thus, body 840 operates as a jet-booster basing on the Venturi effect occurring in the imaginary tunnel adjacent to body 840's surfaces.

[0661] 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.

Jet-Boosters Based on the De Laval-Like Jet-Effect

[0662] Secondly, consider a case, when airfoil body 840 flies relatively slowly, such that sliding sub-portions 853 passes 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 the 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.*. 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: [0663] M.sub.861<M.sub.868<M.sub.*, [0664] M.sub.863<M.sub.868<M.sub.*, [0665] M.sub.863<M.sub.864=M.sub.*, [0666] M.sub.861<M.sub.864=M.sub.*, and [0667] 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. 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 enhanced de Laval-like jet-effect accompanied by extra-cooling and extra-acceleration of air portion 857. This is one more teaching of the present invention.

[0668] A practical application of the phenomenon that, under certain conditions, outflowing portion 857 has an M-velocity higher than the specific M-velocity is one of the primary teachings of the present invention.

[0669] 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.

[0670] Thirdly, consider a case, when airfoil body 840's shape is optimized using the condition of flow continuity Eq. (6.0) 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 the condition of flow continuity Eq. (6.0), 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: [0671] M.sub.861<M.sub.868=M.sub.*, [0672] M.sub.863>M.sub.868=M.sub.*, [0673] M.sub.863>M.sub.864=M.sub.*, [0674] M.sub.861<M.sub.864=M.sub.*, and [0675] 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.

[0676] Fourthly, consider a case, when airfoil body 840's shape is optimized using the condition of flow continuity Eq. (6.0) 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 the condition of flow continuity Eq. (6.0), the de Laval-like retarding-effect occurs in the imaginary convergent-divergent tunnel formed by streamlines 842. Namely, shrinking air portions 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: [0677] M.sub.861>M.sub.868=M.sub.*, [0678] M.sub.863<M.sub.868=M.sub.*, [0679] M.sub.863<M.sub.864=M.sub.*, [0680] M.sub.861>M.sub.864=M.sub.*, and [0681] 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.

[0682] 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: [0683] a method for an airfoil body shape design, based on the condition of flow continuity Eq. (6.0) 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; [0684] 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; [0685] 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; [0686] 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 the 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 [0687] the described convergent-divergent jet-nozzles can be applicable to many apparatuses using mechanical and heat energy, provided by flowing gas or liquid.

Two-Stage Operation of the Coanda-Jet-Effect

[0688] FIG. 8c is divided into two parts: Case (A) and Case (B).

[0689] FIG. 8c Case (A) 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.

[0690] For simplicity and without loss of reasoning, each airfoil body 850 and 860 has the shape of an elongated drop 840 described above referring 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.

[0691] 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 the condition of flow continuity Eq. (6.0), sub-portions 852 of flowing fluid (for instance and without loss of generality, the flowing fluid is airflow) 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 the condition of flow continuity Eq. (6.0), air sub-portions 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-portions 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 a not-optimized shape, flies in an 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.

[0692] FIG. 8c Case (B) is a schematic illustration of a sectional cut of flying actually-airfoil wings 850.B and 860.B in a sagittal plane. The flying actually-airfoil wings 850.B and 860.B are arranged to meet and act on an oncoming portion 851B of flowing fluid sequentially (for instance and without loss of generality, the flowing fluid is airflow). In view of the foregoing description referring to FIG. 8c Case (A), it becomes evident that, in particular, considering a tandem 880.B of two airfoil bodies consolidated as a whole embodied in the form of actually-airfoil wings 850.B and 860.B (for instance, each of which similar to that described hereinabove referring to FIG. 8a) will provide the described specific effect of acceleration and cooling of the airflow portion 851.B originally oncoming faster than with the specific M-velocity M.sub.*. The tandem 880.B comprises all the features of the flying airfoil bodies 850 and 860 of Case (A), and, in contrast to Case (A), the two airfoil bodies, namely, the two actually-airfoil wings 850.B and 860.B, have an asymmetry relative to the horizontal plane 841.B.

[0693] The reference numerals are as follows: [0694] 851.B is an oncoming flow portion yet to be subjected to an action of the tandem 880.B of two actually-airfoil wings 850.B and 860.B consolidated as a whole; [0695] 852.B1 and 852.B2 are sub-portions of the oncoming flow portion 851.B in positions where, when running on the first met local convexity 869.B1 and 869.B2, correspondingly, subjected to convergence above and under the tandem 880.B; [0696] 868.B1 and 868.B2 are narrowed cross-sections of the locally-minimal cross-sectional areas, correspondingly, above and under the first met local convexity: 869.B1 and 869.B2, of the tandem 880.B; [0697] 853.B1 and 853.B2 are sub-portions of the oncoming flow portion 851.B in positions where, when flowing adjacent to the first met local convexity: 869.B1 and 869.B2, correspondingly, subjected to narrowing to have narrowed cross-sections 868.B1 and 868.B2 of the locally-minimal cross-sectional areas, correspondingly, above and under the first met local convexity: 869.B1 and 869.B2, of the tandem 880.B; [0698] 854.B1 and 854.B2 are sub-portions of the oncoming flow portion 851.B in positions where, when passing the first met local convexity: 869.B1 and 869.B2, correspondingly, subjected to divergence above and under the tandem 880.B; [0699] 852.B3 and 852.B4 are sub-portions of the oncoming flow portion 851.B in positions where, when running on the second met local convexity: 869.B3 and 869.B4, correspondingly, subjected to convergence above and under the tandem 880.B; [0700] 868.B3 and 868.B4 are narrowed cross-sections of the locally-minimal cross-sectional areas, correspondingly, above and under the second met local convexity: 869.B3 and 869.B4, of the tandem 880.B; and [0701] 854.B3 and 854.B4 are sub-portions of the oncoming flow portion 851.B in positions where, when passing the second met local convexity: 869.B3 and 869.B4, correspondingly, subjected to divergence above and under the tandem 880.B.

[0702] The profiles of the two actually-airfoil wings 850.B and 860.B are elaborated to meet the oncoming flow portion 851.B originally oncoming faster than with the specific M-velocity M.sub.* such that the two boundary layers composed of the sub-portions, flowing above and under the tandem 880.B, correspondingly, both, when subjected to action by the tandem 880.B, become subjected to a two-stage convergence-divergence accompanying first, by the triggered de Laval retarding-effect and then by the triggered de Laval jet-effect. Borders of the two boundary layers are schematically marked by double-dot dashed lines 842.B1 and 842B2 symbolizing imaginary, in general, curved surfaces formed by streamlines bordering the portion 581.B above and under the tandem 880.B, correspondingly; without loss of generality, the surfaces are indicated as being almost plane and separating, on the one hand, the two two-stage convergent-divergent boundary layers composed of sub-portions of the portion 581.B, which are substantially deforming as moving along the tandem 880.B, and, on the other hand, portions of the ambient flowing fluid which remain relatively weakly deformed. The triggering of the de Laval retarding-effects occurs when the retarding of sub-portions 852.B1 and 852.B2 are such that the sub-portions 853.B1 and 853.B2 cross the narrowed cross-sections 868.B1 and 868.B2 of the locally-minimal cross-sectional areas, correspondingly, with the specific M-velocity M.sub.*; and the triggering of the de Laval jet-effects occurs when the acceleration of sub-portions 852.B3 and 852.B4 are such that the sub-portions 853.B3 and 853.B4 cross the narrowed cross-sections 868.B3 and 868.B4 of the locally-minimal cross-sectional areas, correspondingly, again, with the specific M-velocity M.sub.*.

The asymmetry of the tandem 880.B relative to the horizontal plane 841.B causes that: [0703] on the one hand, as soon as the upper-side outlet sub-portion 854.B3 is wider than the upper-side inlet sub-portion 852.B1, integrally, the upper-side sub-portion becomes accelerated, as it is described hereinabove in the sub-paragraph “Two-Stage Convergent-Divergent Jet-Nozzle” referring to FIG. 6c; and [0704] on the other hand, since the lower-side outlet sub-portion 854.B4 is narrower than the lower-side inlet sub-portion 852.B2, integrally, the lower-side sub-portion remains retarded.
Such an action of the tandem 880.B on the sub-portions of the relatively fast oncoming flow portion 851.B, which (the action) is imbalanced relative to the horizontal plane 841B, originates a resulting upwardly-vectored lift-force cumulatively acting on the tandem 880.B, that is also one of the primary teachings of the present invention.

[0705] FIG. 8d is a schematic illustration of two-stage airfoil wings, constructed according to the principles of the present invention: (A) a two-stage wing 870 having a side-view sectional double-humped airfoil profile 871, and (B) a two-stage wing 8d having a side-view sectional classical airfoil profile and modified by supplying with the multi-layer TE device 8d.TED.

[0706] In FIG. 8d (A), the orientation of the double-humped airfoil profile 871 determines a sagittal axis 871.0, in turn, oriented horizontally. The two-stage double-humped airfoil wing 870 comprises two withers: forward 872 and rear 873, separated by concavity 874. The lift-force force originated by the profile is analyzed, considering the flying M-velocity which is higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach, i.e. when the lift-force, originated by a classical wing 10.A described hereinabove the subparagraph “Airfoil Wing (definition of attack angle)” referring to FIG. 1g Case (A), is negative.

[0707] An oncoming flow portion 875 runs at the double-humped airfoil wing 870, becomes a boundary layer moving adjacent to the upper-side surface of the double-humped airfoil wing 870 under an imaginary surface, which, in a sagittal sectional plane, is indicated by a double-dot dashed line 871.1 symbolizing an imaginary, in general, the curved surface formed by streamlines bordering the portion 875 above the double-humped airfoil 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 double-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 double-humped airfoil profile 871 causes that the cross-sectional area of portion 875 is varying as portion 875 moves over wing 870 as the boundary layer under the imaginary surface 871.1. 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. Thus, there are two convergent-divergent portions of the boundary layer moving adjacent the upper-side surface of the double-humped airfoil wing 870: [0708] first, upstream relative to concavity 874, comprising positions 802, 803, 804, and 805 when flowing over the forward withers 872, and [0709] second, downstream relative to concavity 874, comprising positions 805, 806, 807, 808, and 809 when flowing over the rear withers 873.
Each of the two convergent-divergent portions of the boundary layer is elaborated according to the condition of flow continuity Eq. (6.0) providing for gradually smooth changes of M-velocity to suppress undesired turbulences.

[0710] According to the condition of flow continuity Eq. (6.0), portion 875, as the boundary layer moving under the imaginary surface 871.1, is subjected to the de Laval-like jet-effect and the de Laval-like retarding-effect such that: [0711] 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; [0712] 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; [0713] 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; [0714] 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; [0715] 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; [0716] 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, [0717] 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 can be used as a jet-booster based on the de Laval-like jet-effect, operating at high velocities. In general, the use of a double-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.

[0718] In view of the foregoing description referring to FIG. 8d (A), 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. One of the primary advantages of a double-humped airfoil wing is that, in contrast to a classic wing, the double-humped airfoil wing 870 being stationary (not-variably) configured-and-oriented has a positive lift-force as for low M-velocities and for high M-velocities.

[0719] In view of the foregoing descriptions referring to FIGS. 8a, 8c, and 8d (A), it will be also evident to a person skilled in the art that a pair of actually-airfoil wings (i.e. having sharp trailing ends adapted to provide laminarity of air sub-portions outflowing downstream behind the sharp trailing ends), being arranged in-line along a sagittal axis one downstream behind the other and combined as a whole being stationary (not-variably) configured-and-oriented, can function similar to a double-humped airfoil wing 870 to provide a positive lift-force as for low M-velocities as well as for high M-velocities. Thus, the tandem 880.B of two airfoil bodies embodied in the form of actually-airfoil wings 850.B and 860.B consolidated as a whole (FIG. 8c Case (B)) can be interpreted as a broken double-humped airfoil wing.

[0720] In view of the foregoing descriptions referring to FIGS. 6c, 7d, Sc, and 8d (A), 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)}, [0721] 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, [0722] a specifically-shaped body, having a double-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.

[0723] In FIG. 8d (B), it is shown a schematic drawing of a modified airfoil wing 8d, supplied with the multi-layer TE device 8d.TED built-in between the upper-side and lower-side surfaces of the modified airfoil wing 8d. The modified airfoil wing 8d has a side-view sectional classical airfoil profile, the orientation of which determines a sagittal axis 8d.0 oriented horizontally. For the purpose of the comparison between two wings: the double-humped airfoil wing 810 and the modified airfoil wing 8d, [0724] when the flying M-velocity is higher than the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)}≈0.5345 Mach;
an oncoming flow portion 8d.5 runs at the modified airfoil wing 8d, becomes a boundary layer moving adjacent to the upper-side surface of the airfoil wing 870 under an imaginary surface, which, in a sagittal sectional plane, is indicated by a double-dot dashed line 8d.1 symbolizing an imaginary, in general, the curved surface formed by streamlines bordering the portion 8d.5 above the airfoil wing 8d, and passes positions: 8d.1, 8d.2, 8d.3, 8d.4, 8d.5, 8d.6, 8d.7, 8d.8, and 8d.9 sequentially with associated M-velocities: M.sub.D1, M.sub.D2, M.sub.D3, M.sub.D4, M.sub.D5, M.sub.D6, M.sub.D7, M.sub.D8, and M.sub.D9, correspondingly. The temperature distribution along the upper-side surface is forcibly controlled by the multi-layer TE device 8d.TED such that as the flow moves nearby above the modified airfoil wing 8d: [0725] when crossing the positions 8d.02, 8d.03, and 8d.04, the temperature is gradually increasing thereby imitating the flow convergence and divergence when moving within a de Laval tube similar to the case when the flow moves nearby above the double-humped airfoil wing 870 crossing the positions 802, 803, and 804, correspondingly; and [0726] after reaching the position 8d.05 and further, when crossing the positions 8d.06, 8d.07, 8d.08, and 8d.09, the temperature is gradually decreasing thereby imitating the flow convergence and divergence when moving within a de Laval tube similar to the case when the flow moves nearby above the double-humped airfoil wing 870 crossing the positions 806, 807, 808, and 809, correspondingly.
An advantage of the modified airfoil wing 8d over the double-humped airfoil wing 870 is that the modified airfoil wing 8d provides for all the useful properties of the double-humped airfoil wing 870 in a wide range of velocities, wherein all the useful properties are controllably improved using degrees of freedom of the multi-layer TE device 8d.TED. While the overall geometry of the double-humped airfoil wing 870 is optimized to be adapted to the certain M-velocity M.sub.875 of oncoming flow 875, the modified airfoil wing 8d is capable to be optimally adapted to an arbitrary M-velocity M.sub.8d.5 of oncoming flow portion 8d.5. For this purpose, the forcibly established distribution of the temperature difference ΔT.sub.8d(x) between the upper-side and lower-side boundary layers around the modified airfoil wing 8d is defined as:

[00024] $Δ T_{8 d} (x) = Δ T_{870} (x) \times {[\frac{M_{8 d .5}}{M_{875}}]}^{2},$

where ΔT.sub.870(x) is the distributed original temperature difference between the upper-side and lower-side boundary layers specified when designing the overall geometrical configuration of the double-humped airfoil wing 870 considering the mentioned certain M-velocity M.sub.875 of oncoming flow 875.

Cascaded Jet-Boosters

[0727] 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 and forcedly distributed temperature of the elongated drops is optimized using the condition of flow continuity Eq. (6.0) 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 referring 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.

[0728] In view of the foregoing description referring to FIG. 9a, it will be evident to a person skilled in the art that: [0729] 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; [0730] 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; [0731] 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; [0732] 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 [0733] 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 can be used to power a Peltier-element operating as a thermoelectric generator producing electricity.

[0734] 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 to 9016 due to the electromagnetic jet-effect.

[0735] 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 and forcedly distributed temperature, similar, for example, to that 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 and forcedly distributed temperature are optimized using the condition of flow continuity Eq. (6.0) 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. 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 referring to FIG. 9a, considering a sequential multi-stage cascade of in-line arranged airfoil bodies, each having the shape of an elongated drop.

[0736] 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 and forcedly distributed temperature, for example, similar to described above referring to FIG. 8a. Airfoil profile 937, also shown separately above and to the left in an enlarged scale, and forcedly distributed temperature, both are optimized using the condition of flow continuity Eq. (6.0) 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 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.

[0737] Moreover, the two spirals 931 and 932 have counter 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.

[0738] In view of the foregoing description of FIGS. 9a, 9b, and 9c, it will be evident to a person skilled in the art that: [0739] 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 [0740] 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 the 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 a special 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's mass 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.1×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.

[0741] 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: [0742] 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), [0743] in the case, when the elemental jet-boosters operate independently, that occurs, [0744] if the elemental jet-boosters are arranged in parallel, or [0745] 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; [0746] or, alternatively, [0747] 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], [0748] 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: [0749] the condition W.sub.sequential<W.sub.parallel is satisfied for N≤8; [0750] the condition W.sub.sequential>W.sub.parallel is satisfied for N≥9; [0751] the condition W.sub.sequential>2W.sub.parallel is satisfied for N≥13; [0752] the condition W.sub.sequential>3W.sub.parallel is satisfied for N≥15; and [0753] the condition W.sub.sequential>4W.sub.parallel is satisfied for N≥16.

[0754] 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: [0755] 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; [0756] 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 the velocity u.sub.jetstream=u.sub.income×F.sup.N [F.sup.N=1.097.sup.15≈4] and having the resulting effective frontal 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 [0757] 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.consume.

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 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.

[0758] 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 half of the 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: [0759] 9011, 9013, 9014, 9015, and 9016 as shown in FIG. 9a; or [0760] a multi-stage cascade of outer and nested airfoil rings 920 as shown in FIG. 9b; or [0761] 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.

Jet-Turbine as Improved Wind-Turbine

[0762] FIG. 9g is a schematic drawing of a jet-rotor of modified improved wind-turbine, called also a jet-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.

[0763] Modified improved wind-turbine or jet-turbine 9.0 comprises: [0764] axle 9.2 oriented along sagittal axis 9.21 codirected with fast airflow 9.1, [0765] identical asymmetrical biconvex actually-airfoil blades 9.3, attached to axle 9.2; and [0766] an engine, which is not shown here, having a stator and rotatable shaft; the engine is capable of transforming the power of the forced mechanic rotational motion 9.4 of axle 9.2 into electric power.

[0767] The primary feature, making the jet-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 jet-turbine 9.0 has asymmetrical biconvex wing-like actually-airfoil blades 9.3: [0768] having opposite convex sides 9.31 and 9.32 with withers differing in convexity, and [0769] being oriented along and so adapted to the incoming fast airflow jetstream 9.11 headway motion.
Thereby configured and oriented blades provide the zero attack angle: [0770] to exclude or at least to minimize the impact by the incoming fast airflow jetstream 9.11, but [0771] to provide an interaction with the fast airflow jetstream 9.11 by the Coanda-jet-effect only, thereby resulting in acceleration and cooling of outflowing jetstream 9.6 and resulting in lift-forces, acting on identical biconvex actually-airfoil blades 9.3 and being imbalanced 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: [0772] by the mechanism of operation, that is the Coanda-jet-effect but not the impact; and [0773] by the power source of operation, that is the warmth but not the kinetic power of airflow.
Also, in contrast to a kind of the standard wind-turbines having wing-like blades moving around a vertical axis, the proposed jet-turbine 9.0 is specifically characterized by the excluding of varying poorly-streamlined positions of the wing-like blades. As well, in contrast to the standard wind-turbines, the productivity of the proposed jet-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.

[0774] In view of the foregoing description referring to FIG. 9g, it will be evident to a person skilled in the art that jet-turbine 9.0 comprising: [0775] the biconvex airfoil blades, having a wing-like sectional contour with a longer so-called chord of wing, and/or [0776] 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 jet-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.

[0777] Moreover, at least one of the profiles 9.31 and 9.32 is implemented to provide the enhanced de Laval 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.

[0778] 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 double-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 enhanced de Laval jet-effect. This provides for extra-increased lift-forces acting in unison and in the same direction of rotation and so rotating axle 9.2. In this case, the extra-efficiency of the modified improved wind-turbine is expected in a wide range of velocities.

[0779] FIG. 9h is a schematic drawing comprising the side-view and front view of a jet-rotor of jet-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. An engine of the jet-turbine, which (the engine) having a stator and rotatable shaft, is not shown here. Axle 9.73, collinear with sagittal axis 9.74, is oriented to be codirected with the headway motion of the relatively fast airflow 9.70. In relation to all the principal features, the jet-turbine 9.7 is similar to the jet-turbine 9.0, described hereinabove referring to FIG. 9g, but now, referring to the aforementioned optional diversity of the implementation of the principal features, the biconvex actually-airfoil blades, which have 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.

[0780] In view of the foregoing description referring to FIGS. 9g and 9h, it will be evident to a person skilled in the art that jet-turbine 9.0 or 9.7, when attached to a flying aircraft, is capable of efficient harvesting of the electric power from the ambient air warmth.

[0781] 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 jet-turbines 9.0 or 9.7, arranged sequentially one downstream after another [not shown hem], results in the 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 production of electricity.

[0782] In view of the foregoing description referring to FIGS. 9g and 9h in combination with the foregoing description of subparagraphs “Point of Sail” 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 jet-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.

[0783] Furthermore, in view of the foregoing description referring to FIGS. 9g and 9h, it will be evident to a person skilled in the art that jet-rotor 9.7 having relatively massive actually-airfoil wings, [0784] when being attached to a body moving in a fluid and being capable of free rotation around the sagittal axis 9.74 due to the self-originated lift-forces acting on all the massive wings in unison and in the same direction of rotation,
creates the gyroscopic effect that is defined as a tendency of the moving body to maintain a steady direction collinear with the sagittal axis 9.74 being the axis of the massive wings rotation and is manifested as a resistance to gusty fluctuations of motion of the ambient fluid, wherein the energy to generate the desired gyroscopic effect improving ballistic properties of the moving body is harvested from the ambient fluid warmth due to the Coanda-jet-effect.

Jet-Ventilator and Jet-Propeller

[0785] FIG. 9j is a schematic drawing of a modified improved ventilator, called also a jet-ventilator, 9J.0, constructed according to the principles of the present invention to create a headway laminarly moving flow. The jet-ventilator 9J.0 comprises a jet-rotor, which also is marked by numeral 9J.0, and a motor, which is not shown here, having a stator and rotatable shaft. The motor, being powered by either a burned fuel or electrical power, forcedly rotates the rotatable shaft and, thereby, the jet-rotor 9J.0.

[0786] One of the specifics of the jet-ventilator 9J.0 is that blades 9J.1, having a profile 9J.2 similar to the profile of actually-airfoil biconvex wing 810 described hereinabove referring to FIG. 8a, are configured to be actually-airfoil and, when rotating, oriented to run over air portions 9J.6 (yet to be subjected to a motion) under the zero attack angle and to act on the air portions 9J.6 due to the Coanda-effect only. As the air portions 9J.6, when subjected to the Coanda-effect, originate lift-force 9J.3 acting on the blades 9J.1, the blades 9J.1 push-off the air portions 9J.6 in the opposite direction collinear to sagittal axis 9J.7 according to Newton's Third Law. Thereby, headway-forwarding air portions become a headway-forwarding laminar no-whirling outflow 9J.5 created by the jet-ventilator 9J.0. As the used blades 9J.1 are actually-airfoil, relatively low power consumption can provide a relatively fast rotation 9J.9 of the blades 9J.1, wherein the velocity of the fast rotation 9J.9 is in conformance with an optimal configuration 9J.2 of the actually-airfoil blades 9J.1. Since the desired acceleration of the outflow occurs due to the Coanda-effect only, the method of accelerating the outflow allows for significantly reducing energy consumption compared with the classical technique based on the impact of the blades. It will be evident for a commonly educated person, that the concept of jet-ventilator 9J.0 is applicable to any fluid either gas or liquid. A disadvantage of the technique to create the laminar no-whirling flow 9J.5 is that the relatively fast rotation 9J.9 of the blades 9J.1 produces relatively slow laminar no-whirling flow 9J.5.

[0787] FIG. 9k is a schematic drawing of jet-propeller 9K.0, constructed according to the principles of the present invention. The jet-propeller 9K.0 comprises a jet-rotor, which also is marked by numeral 9K.0, and a motor, which is not shown here, having a stator and rotatable shaft. The motor, being powered by either a burned fuel or electrical power, forcedly rotates the rotatable shaft and, thereby, the jet-rotor 9K.0. As the function difference between jet-propeller 9K.0 and jet-ventilator 9J.0 is that, while the jet-rotor of jet-ventilator 9J.0 acts to initially motionless air portions 9J.6, the jet-rotor of jet-propeller 9K.0 acts to airflow 9K.6 oncoming to blades with a certain velocity; so, the primary constructive difference between jet-propeller 9K.0 and jet-ventilator 9J.0 is in the orientation of blades. Namely, blades 9K.1 of jet-propeller 9K.0 are turned on a certain angle 9K.8, called also pitch, such that, when rotating with a certain rate 9K.9, to run over oncoming airflow 9K.6 under the zero attack angle and to act on oncoming airflow 9K.6 due to the Coanda-effect only. As the lift-force 9K.3 acting on wings 9K.1 has a component directed collinearly to sagittal axis 9K.7 against the direction of the oncoming airflow 9K.6, the oncoming airflow 9K.6 becomes subjected to acceleration according to Newton's Third Law, thereby forming, resulting headway-forwarding outflow 9K.5. As the certain velocity of oncoming airflow 9K.6, the certain rate of blades 9K.1 rotation 9K.9, and the certain angle 9K.8 of blades 9K.1 orientation, all are interrelated, one can adapt the blades 9K.1 rotation rate 9K.9 and angle of orientation 9K.8 to the oncoming flow velocity 9K.6 to provide the zero attack angle to act on oncoming airflow 91K.6 due to the Coanda-effect only. When all the parameters are matched, the resulting headway-forwarding outflow 9K.5 accelerated by jet-propeller 91K.0 is laminar and no-whirling.

[0788] In view of the foregoing description referring to FIGS. 9j and 9k, it becomes evident, that: [0789] jet-propeller 9K.0 can comprise a variable pitch being capable of being adapted to the velocity of oncoming flow and rotation rate; [0790] jet-ventilator 9J.0 can be interpreted as a particular case of jet-propeller 9K.0, the pitch of which is adapted to initially stationary fluid; [0791] jet-ventilator 9J.0, pitch 9J.8 of which providing the zero attack angle of meeting stationary portions of air, and jet-propeller 9K.0, pitch 9K.8 of which being adapted to the velocity of airflow 9J.5 created by jet-ventilator 9J.0, can be arranged in-line: the jet-propeller after the jet-ventilator, thereby forming a system that as a whole performs an improved jet-ventilator providing for boosted outflow; and [0792] since the blades of jet-propeller 9K.0, when moving, meet the ambient fluid at the zero attack angle and so, on the one hand, consume power to overcome a minimized drag and, on the other hand, produce the useful-beneficial power of accelerated outflow at the expense of ambient warmth due to the Coanda-jet-effect, a net-efficiency higher than 100% becomes reachable.

[0793] Reference is now made to FIG. 9L. FIG. 9L is a schematic illustration of a multi-module jet-ventilator 9L.0, constructed according to the principles of the present invention to create a boosted headway-forwarding laminar no-whirling 9L.5. The multi-module jet-ventilator 9L.0 comprises a tuple of modules 9L.01 to 9L.07 attached to a common shaft. Each of the modules 9L.01 to 9L.07 is characterized by an individual pitch, wherein: [0794] The “zero” pitch of the first module 9L.01 provides for that, when the rotating blades of the first module 9L.01 run over the originally stationary portion of air 9L.6 at the zero attack angle, the first module 9L.01 functions as jet-ventilator 9J.0 described hereinabove referring to FIG. 9j; [0795] A relatively small pitch of the second module 9L.02 provides for that, when the rotating blades of the first module 9L.02 run over portions of a relatively slow flow originated by the first module 9L.01 at the zero attack angle, i.e. the second module 9L.02 functions as jet-ventilator 9K.0 adapted to a certain oncoming flow as described hereinabove referring to FIG. 9k; [0796] The individual pitch of each next module: 9L.03 to 9L.07, provides for that, when the rotating blades of the next module: 9L.03 to 9L.07 run over portions of a flow originated the previous module: 9L.02 to 9L.06, correspondingly, at the zero attack angle, i.e. all each of the modules 9L.03 to 9L.07 functions as jet-ventilator 9K.0 adapted to an associated oncoming flow as described hereinabove referring to FIG. 9k.

[0797] As a result of all the modules 9L.01 to 9L.07 operation as a whole, the resulting headway-forwarding laminar no-whirling outflow 9L.5 becomes accelerated reaching a relatively high velocity vectored collinearly to sagittal axis 9L.7.

[0798] FIG. 9m is a schematic illustration of a cascade 9M.0 of multi-module jet-ventilator 9M.01 and two multi-module propellers 9M.02 and 9M.03 aggregated along the common sagittal axis 9M.7. The cascade 9M.0 is constructed according to the principles of the present invention, wherein the multi-module jet-ventilator 9L.0 and multi-module propellers 9M.02 and 9M.03, each comprises a tuple of modules attached to a common shaft. The multi-module jet-ventilator 9M.01 acts on an initially stationary portion of fluid 9M.6 and creates outflow 9M.51, which, in turn, becomes oncoming flow 9M.51 blowing the multi-module jet-propeller 9M.02. The multi-module jet-propeller 9M.02 acts on the oncoming flow 9M.51 and creates outflow 9M.52, which, in turn, becomes oncoming flow 9M.52 blowing the multi-module jet-propeller 9M.03. The multi-module jet-propeller 9M.03 acts on the oncoming flow 9M.52 and creates the resulting outflow 9M.53. Without loss of generality, the tuple of the multi-module jet-ventilator 9M.01 is a triplet of modules attached to a common shaft. As well, again, without loss of generality, a tuple of each of jet-propellers 9M.02 and 9M.03 is a triplet of modules attached to a common shaft. Each of the mentioned modules comprises three sets of blades, wherein each of the sets is characterized by an individual pitch. The pitches of modules and rates of rotations 9M.91, 9M.92, and 9M.93 are chosen such that all the blades run over portions of oncoming flow at the zero attack angle. Optionally, blades of jet-propeller 9M.02 are configured for rotations 9M.91 and 9M.92 in mutually-opposite directions: clockwise and contrary-clockwise, correspondingly. The alternating directions of the rotations of in-line arranged jet-rotors are preferred to compensate for the unwanted whirling of flow. Although the unwanted whirling is purposely suppressed by excluding or at least minimizing the impact by blades, it (the unwanted whirling) can be originated due to other effects such as skin-friction between the flow and blades as well as jet-thrust described hereinabove in subparagraphs “Point of Sail” and “Flying Bird”, both with the reference to prior art FIG. 1i.

Heat-Turbine and Jet-Transformer

[0799] FIG. 9n is a schematic illustration of a concept to transform the ambient warmth into electricity. The concept is embodied as a heat-turbine 9n.H and jet-transformer 9n.J comprising: [0800] a laminar flow maker 9n.2, in turn, comprising at least one of [0801] a shaped heater 9n.21, conceptually, having a geometry of convex-concave corpus having airfoil outer walls 9n.211 and paraboloidal inner wall 9n.213 and being supplied by a point heater 9n.212 located in the focus of the paraboloidal inner wall 9n.213; [0802] a shaped jet-ventilator 9n.22, conceptually, embodied as a multi-module jet-ventilator described hereinabove in the subparagraph Jet-Ventilator and Jet-Propeller referring to FIGS. 9J, 9k, 9L, and 9m [here, for simplicity of the drawing, a one-module jet-ventilator 9n22 is shown]; [0803] a specifically shaped pipe 9n.1 having the optimized convergent-divergent inner tunnel, described hereinabove in sub-paragraph “Convergent-Divergent Jet-Nozzle” with reference to FIG. 6a; namely, the convergent-divergent inner tunnel, elevated above the ground to allow for the ambient air 9n.41 entering the optimized convergent-divergent inner tunnel, comprises forcedly controllable thermoelectric devices 9n.TED built-in into walls 9n.WALLS such that the geometry of the tunnel, temperature distribution along the tunnel, and velocity of the upward laminar flow become interrelated according to the condition of flow continuity Eq. (6.0); and [0804] at least one jet-turbine 9n.3, designed as the jet-turbine 9.7 described hereinabove referring to FIG. 9h;
all, constructed according to the principles of the present invention.
The Case when the Shaped Heater 9n.21 is Used in the Heat-Turbine 9n.H

[0805] The specifically shaped pipe 9n.1 is upward oriented. The point heater 9n.212 supplies the heat energy to a fluid portion adjacent to the focus of the parabolically-concave surface 9n.213 of the shaped heater 9n.21's convex-concave corpus, thereby, on the one hand, to trigger the Archimedes' upward-vectored force lifting the heated fluid portion and, on the other hand, to align the airflow 9n.42 upward along the vertical axis 9n.51 which is a sagittal axis, for the case. The upward airflow 9n.42 is relatively slow and substantially-laminar. The optimized convergent-divergent inner tunnel of the specifically shaped pipe 9n.1, supplied with forcedly controllable thermoelectric devices 9n.TED built-in into walls 9n.WALLS, is designed according to the condition of flow continuity Eq. (6.0) to provide for substantial suppression of jumps of the air thermodynamic parameters and, thereby, to provide for the substantial acceleration of the airflow 9n.42, 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: [0806] the temperature above the exhaust 9n.54 equal T.sub.e that is lower than the temperature T.sub.a of the ambient air; the condition T.sub.e=T.sub.a is for the worst-case estimation; [0807] the temperature near the level 9n.52 equal T.sub.0, and [0808] the temperature near the narrow throat 9n.53 equal T.sub.*,
equation (7.1c), described hereinabove referring to FIG. 7a, says that: [0809] to obtain the enhanced 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 [0810] to provide that the temperature T.sub.e of outflowing stream 9n.44 above the exhaust 9n.54 become equal to the temperature of ambient air, 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.
Hence, providing the heating of air near the level 9n.52 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 point heaters 9n.212, triggers the enhanced de Laval jet-effect transforming the warmth of the moving airflow into the acquired kinetic power of the airflow. 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.a), where V is the volume of 1 cube meter, ρ is the air mass 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.

[0811] As the mentioned assumed condition allows to accelerate the airflow portion 9n.54 up to the specific M-velocity M.sub.*=√{square root over ((γ−1)/γ)} near the narrow throat 9n.53 and to accelerate the airflow portion 9n.54 up to almost the speed of sound (i.e. the exhaust M-velocity is of M.sub.e≈1), then, an exemplary estimation is as follows: [0812] the acquired kinetic energy, K.sub.e, of the outflowing airflow portion 9n.54, 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 [0813] the acquired kinetic energy, K.sub.*, of the airflow portion 9n.54, 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.

[0814] It will be evident to a commonly educated person that, if not to use the optimized convergent-divergent inner tunnel, designed according to the condition of flow continuity Eq. (6.0), 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.

[0815] The jet-turbine 9n.3 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 9n.3 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 a boosted trigger of the lift-force rotating the improved wind-turbine. Moreover, optionally, in-line arranged several jet-turbines 9n.3 provide for a multi-stage repeatedly harvesting of electricity from the same airflow portion.

[0816] It will be evident to a person who has studied the present invention that both the outer convex wall 9n.211 and the inner wall 9n.213 can be supplied with built-in matrix thermoelectric devices to control laminarity of the entering heated flow 9n.42.

The Case when the Shaped Jet-Ventilator 9n.22 is Used in Jet-Transformer 9n.J

[0817] The substantially-laminar airflow 9n.42 enters the specifically shaped pipe 9n.1 with a certain velocity u.sub.in. The optimized convergent-divergent inner tunnel of the specifically shaped pipe 9n.1, supplied with forcedly controllable thermoelectric devices 9n.TED built-in into walls 9n.WALLS, is designed according to the condition of flow continuity Eq. (6.0) such to be adapted to the velocity u.sub.in to result in the substantial acceleration of the airflow 9n.42, laminarly and so noseless streaming along the optimized convergent-divergent inner tunnel; wherein, in this case, the orientation of the sagittal axis 9n.51 is not obligatory upward.

Levitating Apparatus Imitating Effects of Taking-Off of Bird and Insect

[0818] FIG. 9o is a schematic illustration of a levitating apparatus 9o.0 comprising: [0819] a shaped propeller 9o.1, conceptually, embodied as a multi-module jet-ventilator [here, for simplicity of the drawing, a pair of counter-rotating one-module jet-ventilators is shown; the rotations are indicated by the circle arrows 9o.13 and 9o.14] described hereinabove in the subparagraph Jet-Ventilator and Jet-Propeller referring to FIGS. 9j, 9k, 9L, and 9m; and [0820] a capsule 9o.2 having a dominantly-airfoil overall shape and being optionally scaled to fit a person [a sculpture 9o.3 is shown instead of the person].
The wings 9o.11 and 9o.12 of the shaped propeller 9o.1 are supplied with thermoelectric devices as described hereinabove in subparagraphs “Modified Symmetrical Wing” and “Shaped Wing as a Convergent-Divergent Jet-Nozzle” referring to FIGS. 8 and 8a such that providing the effective temperature difference ΔT.sub.WING between the upper and lower sides of the wings 9o.11 and 9o.12. Shell 9o.SHELL of the capsule 9o.2 is supplied with a matrix thermoelectric device 9o.TED such that the temperature of the shell 9o.SHELL's outer side is forcedly controlled to be gradually distributed along the axis Z providing the integral temperature difference ΔT.sub.Z,CAPSULE around the ambient temperature τ.sub.AMBIENT. The gradually smoothed curve 9o.4 is in coordinates (T, Z), where the axis-T indicates the temperature. When the wings 9o.11 and 9o.12 are rotating around the vertical axis 9o.AXIS: [0821] while the wings 9o.11 and 9o.12 are subjected to: [0822] the lift-force F.sub.LIFT, that is a measure of the lift-effect of a “cold-blooded” wing, i.e. is provided by the airfoil geometry of the wings 9o.11 and 9o.12, and [0823] the positive contribution ΔF.sub.BIRD to the upward-vectored force, wherein the originated effect of the contribution ΔF.sub.BIRD imitates the effect of taking-off of a bird; [0824] the capsule 9o.2 is subjected to blowing by fresh portions of air triggering the positive contribution ΔF.sub.INSECT to the upward-vectored force, wherein the originated effect of the contribution ΔF.sub.INSECT imitates the effect of taking-off of an insect.
To evaluate the practicality of the flying apparatus 9o.0 for industrial use, exemplary positive contributions ΔF.sub.BIRD and ΔF.sub.INSECT to the upward-vectored force are estimated considering: [0825] the normal ambient air conditions: T=τ.sub.AMBIENT≈300K, P=P.sub.AMBIENT≈100,000 Pa, ρ=ρ.sub.AMBIENT≈1.2 kg/m.sup.3, and γ=7/5; [0826] an exemplary version of the shaped propeller 9o.1 performing a two-module ventilator having two triplets of wings 9o.11 (i.e. 6 wings); [0827] each of the wings 9o.11 has a chord of 0.25 m and a span of 0.5 m; i.e. the total area of the wings is A.sub.WINGS=6×0.25×0.5=0.75 m.sup.2; [0828] the effective temperature difference between the upper and lower sides of the wings is ΔT.sub.WING=−30 C; [0829] the refreshed air portions on the upper and lower sides of the wings are subjected to suddenly originated effective difference in static pressures along the axis Z, indicated by ΔP.sub.WING, interrelated with ΔT.sub.WING according to equation Eq. (1.1b) described hereinabove in the subparagraph “Sound as Complicated Movement in Molecular Fluid” prefacing the reference to FIG. 1n, namely, the ratio (−ΔT.sub.WING)/T≈0.1, the ratio (−ΔP.sub.WING)/P≈0.1×(7/5)/(2/5)=0.35, and so the suddenly originated effective additional static pressure difference is (−ΔP.sub.WING) 0.35×10.sup.5 Pa; [0830] the velocity-dependent suddenness factor, indicated by C.sub.WING, for calculation of the ΔF.sub.BIRD is given by 0.1 as corresponding to the effective velocity u.sub.WING of the wings rotation 9o.12 as fast as 20 m/sec; [0831] the cross-sectional area 9o.21 of a projection of the capsule 9o.2, A.sub.(X,Y),CAPSULE, in a horizontal plane is given by 0.8 m.sup.2; [0832] the integral temperature difference, ΔT.sub.Z,CAPSULE, is given by −30 C; [0833] the refreshed air portions, when flowing around the capsule 9o.2, are subjected to suddenly originated effective difference in static pressures along the axis Z, indicated by ΔP.sub.Z,CAPSULE interrelated with ΔT.sub.Z,CAPSULE as follows: the ratio (−ΔT.sub.Z,CAPSULE)/T≈0.1, the ratio (−ΔP.sub.Z,CAPSULE)/P≈0.1×(7/5)/(2/5)=0.35, and so the suddenly originated additional static pressure difference is (−ΔP.sub.Z,CAPSULE)≈0.35×10.sup.5 Pa; and [0834] the velocity-dependent suddenness factor, indicated by C.sub.CAPSULE, for calculation of the ΔF.sub.INSECT is given by 0.027 as corresponding to the velocity u.sub.BLOW of a flow 9o.15 when blowing the capsule 9o.2 given by 5 m/sec.
Thus, the originated forces are estimated as follows: [0835] the lift-force F.sub.LIFT provided by the geometry of the six wings 9o.11, wherein the geometry is characterized by the coefficient of lift C.sub.L exemplary given by 0.5, is estimated as:

F.sub.LIFT=0.5×ρ×A.sub.WINGS×C.sub.L×u.sub.WING.sup.2≈90N; [0836] the contribution ΔF.sub.BIRD to the upward-vectored force, which (ΔF.sub.BIRD) is a measure of the imitated effect of taking-off of a bird, is:

ΔF.sub.BIRD=(½)×C.sub.WING×A.sub.WINGS×(−ΔP.sub.WING)≈1,427N; [0837] the contribution ΔF.sub.INSECT to the upward-vectored force, which (ΔF.sub.INSECT) is a measure of the imitated effect of taking-off of an insect, is:

ΔF.sub.INSECT=(½)×C.sub.CAPSULE×A.sub.(X,Y),CAPSULE×(−ΔP.sub.Z,CAPSULE)≈385N; [0838] and, thereby, [0839] the accumulated contribution to the upward-vectored force is estimated as (F.sub.LIFT+ΔF.sub.BIRD+ΔF.sub.INSECT)≈1,839 N that is sufficient to raise a mass of 184 kg.
Wherein, concerning power consumption: [0840] to rotate the shaped propeller 9o.1 having wings 9o.11 and 9o.12 oriented to meet the ambient air portions at the zero attack angle dominantly, minimal power consumption is required for overcoming the minimal drag of wings only; and [0841] to support the required temperature differences, ΔT.sub.WING and ΔT.sub.CAPSULE, a 15% net-efficiency of standard Peltier elements determines the required power consumption.
Further, the matrix thermoelectric device 9o.TED is capable of providing for controlled distribution of the shell 9o.SHELL's temperature along the axis X. The gradually smoothed curve 9o.5 is in coordinates (X, T), where: [0842] axis X indicates the horizontal direction; [0843] the maximal frontal cross-sectional area of the capsule 9o.2, indicated by A.sub.(Y,Z),CAPSULE, is given by 2 m.sup.2; [0844] the integral temperature difference between the coordinates X.sub.LEFT and X.sub.RIGHT of the capsule 9o.2 location, indicated by ΔT.sub.X,CAPSULE, is given by 30 C; and [0845] the refreshed air portions, when flowing around the capsule 90.2, are subjected to suddenly originated effective difference in static pressures along the axis X, indicated by ΔP.sub.X,CAPSULE, interrelated with ΔT.sub.X,CAPSULE as follows: the ratio (ΔT.sub.X,CAPSULE)/T≈0.1, the ratio (ΔP.sub.X,CAPSULE)/P≈0.1×(7/5)/(2/5)=0.35, and so the suddenly originated additional static pressure difference is ΔP.sub.X,CAPSULE≈0.35×10.sup.5 Pa.
Thus, the possible thrust 9o.THRUST for a sideward motion is:

ΔF.sub.X,THRUST=(½)×C.sub.CAPSULE×A.sub.(Y,Z),CAPSULE×(−ΔP.sub.Z,CAPSULE)≈950N

that allows moving the mentioned mass of 184 kg with an acceleration of about 5 m/sec.sup.2 in a horizontal direction. The controllable difference between the speeds of counter rotations 9o.13 and 9o.14 provides a controlled rotation of the capsule 9o.2 around the axis 9o.AXIS.

[0846] In view of the foregoing description referring to FIGS. 9n and 9o, it will be evident to a person skilled in the art that: [0847] the levitating apparatus 9o.0 can be further supplied with at least one of the heat-transformer 710.H and the jet-transformer 9n.J having the shaped jet-ventilator 9n.22 and oriented such that the sagittal axis 9n.51 is directed downward and/or sideward; [0848] Instead of Peltier elements (thermoelectric devices 9o.TED), any kind of electric heater and/or cooler (i.e. a thermoelectric device in the broad sense) can be used to control the temperature distribution over the shell 9o.SHELL's, because the inertness of temperature difference controlling is not critical for the steady-established and relatively slow blowing flow 9o.15; and [0849] In general, when allowed tolerances to the temperature difference controlling are relatively big, an electric heater consuming electric power and radiating Jole heat which is interpreted as a trivial thermoelectric device can be used.

In the Claims

[0850] In the claims, reference signs are used to refer to examples in the drawings for the purpose of easier understanding and are not intended to be limiting on the monopoly claimed.

Apparatuses Based on Jet-Effect and Thermoelectric Effect

Inventors

Cpc classification

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H10N10/13

ELECTRICITY

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B64C27/467

PERFORMING OPERATIONS; TRANSPORTING

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H04R1/46

ELECTRICITY

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H10N10/17

ELECTRICITY

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B64C3/14

PERFORMING OPERATIONS; TRANSPORTING

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H02J7/02

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B64C2230/10

PERFORMING OPERATIONS; TRANSPORTING

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B64C3/36

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B64C11/005

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B05B1/3402

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H02J50/15

ELECTRICITY

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B64D27/18

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F15D1/0065

MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

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H04R1/1016

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A61B7/04

HUMAN NECESSITIES

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B64C99/00

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B05B1/24

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H01L35/30

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B05B1/24

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B05B1/34

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B64C3/36

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B64D27/18

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H01L35/32

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H02J50/15

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H02J7/02

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