Vertical takeoff and landing aircraft and gas turbine engine with fan thrust and exhaust thrust delivered downwardly

Abstract

An aircraft airfoil or wing or fuselage MODULE is fitted with a gas turbine engine driving a fan or propeller, in combination with a gaseous pressure accumulator, wherein said fan or propeller and said gaseous pressure accumulator both provide thrust, said fan thrust being provided from a rear of the MODULE via a drop-down thrust vectoring panel and said gaseous pressure accumulator thrust being provided from a fore of said MODULE, wherein the gaseous pressure accumulator is supplied with exhaust from said gas turbine engine and said exhaust is delivered downwardly at a variable angle, and said thrust vectoring panel is a panel with multiple minor panels which vector fan thrust at more than one angle. The gas turbine engine exhaust is delivered forwardly of said fan or propeller exhaust.

Claims

1. An aircraft comprising a travel direction and a prime mover, said prime mover producing an exhaust, said aircraft comprising a forward portion and a rearward portion in relation to said travel direction, said forward portion comprising a forward thrust element and said rearward portion comprising a rearward thrust element, wherein: said forward thrust element is at least one downwardly angled modulated valve or valves in fluid communication with an exhaust of said prime mover; said rearward thrust element is a rotationally or arcuately movable panel in combination with a fan or propeller, wherein; said prime mover passes gases to an accumulation chamber and at least one of said accumulation chamber and said fan or propeller is configured to direct gases at more than one downward direction relative to said travel direction.

2. The aircraft of claim 1 wherein: said forward thrust element is a rotatable valve with at least two thrust delivery angles and said rearward thrust element is a movable panel of a first size that comprises independently movable panels of a second size smaller than said first size and said forward thrust element delivers prime mover exhaust from an internal area of said aircraft.

3. The aircraft of claim 2 wherein said forward thrust element is a cylindrical element rotationally attached to said aircraft, said cylindrical element being rotatable to effect more than one thrust direction, said more than one thrust direction relative to said longitudinal axis and wherein at least one of said rearward thrust element and said forward thrust element expels exhaust derived from said prime mover.

4. The aircraft of claim 3 wherein: said aircraft has a hollow portion within said aircraft and said prime mover resides within said hollow portion.

5. The aircraft of claim 1 wherein: said rearward thrust element comprises at least two deflection vanes or panels that move independently of on another to achieve disparate concurrent angles.

6. The aircraft of claim 1 wherein said rearward thrust element is an extensible panel of a first size that comprises independently movable panels of a second size smaller than said first size, and said rearward thrust element is a fan or propeller, wherein: said prime mover supplies exhaust gases to a gaseous accumulation chamber that delivers pressurized gases to said forward thrust element.

7. The aircraft of claim 1 wherein said prime mover comprises a turbine and a gaseous accumulation chamber that accumulates exhaust from said turbine for use by said forward thrust element.

8. The aircraft of claim 7 wherein said gaseous accumulation chamber comprises an internal hollow space filled with exhaust from said turbine, and within said internal hollow space resides at least one of: said prime mover; a fuel tank; a fuel injection system; a flywheel in combination with electrical elements configured to establish a regenerative braking scheme for said prime mover.

9. The aircraft of claim 1 wherein said prime mover is a flywheel comprising a rotational velocity and further comprising a compressor stage and a turbine stage within or unitary with said flywheel, said compressor stage and said turbine stage locked for rotation together such that said compressor stage and said turbine stage rotate at an equal rotational velocity, one to another.

10. An aircraft comprising a longitudinal axis, below said longitudinal axis is a downward direction and above said longitudinal axis is an upward direction, said aircraft further comprising a longitudinal direction, said longitudinal direction and said aircraft having a direction of travel in which a forward direction is substantially along said longitudinal axis and a rearward direction is in a direction substantially opposite to said forward direction, said aircraft comprising a fuselage or wing, said aircraft further comprising a prime mover, wherein; said fuselage or, alternatively, said wing or, alternatively, said aircraft comprises a forward portion and a rearward portion, said fuselage or said wing or said aircraft comprises: a forwardly residing thrust element that delivers gases in a downward direction; forwardly corresponding to said forward direction along the longitudinal direction and downwardly being in said downward direction which is downward of the longitudinal direction; a rearwardly residing thrust element that delivers gases in a downward direction; wherein; at least one of said forward thrust element and said rearward thrust element is a variable angle gas delivery or gas deflection element that delivers or deflects gases downwardly of said longitudinal axis at a first angle and also at at least one second angle distinct from said first angle relative to said longitudinal axis.

11. The aircraft of claim 10 wherein said forward thrust element is a rotatable valve with at least two distinct thrust delivery angles.

12. The aircraft of claim 10 wherein said rearward thrust element is a movable panel of a first size that comprises independently movable panels of a second size smaller than said first size.

13. The aircraft of claim 12 wherein said forward thrust element delivers gases from an internally hollowed volume of said fuselage or said wing or aircraft.

14. The aircraft of claim 12 wherein said forward thrust element is a cylindrical element rotationally attached to said aircraft, said cylindrical element being rotatable to effect more than one thrust direction, said more than one thrust direction compared to said longitudinal axis.

15. The aircraft of claim 12 wherein at least one of said rearward thrust element and said forward thrust element expels exhaust gases derived from said prime mover.

16. The aircraft of claim 15 wherein said rearward thrust element is a movable panel of a first size that comprises independently movable panels of a second size smaller than said first size.

17. The aircraft of claim 10 wherein said aircraft has a hollow portion within said aircraft, said prime mover residing within said hollow portion.

18. The aircraft of claim 10 wherein said rearward thrust element is a fan or propeller in combination with a panel that moves away from said fan or said propeller, said panel comprising at least two panels that actuate independently from one another to form more than one simultaneous angle of thrust deflection.

19. The aircraft of claim 18 wherein said panel comprises minor vanes that selectively deflect thrust downward.

20. The aircraft of claim 18, wherein said minor vanes comprise at least one first vane and at least one second vane, said at least one first vane and said at least one second vane being selectively movable to different angles relative to each other to effect differential deflection of said gases.

21. The aircraft of claim 10, wherein said forward thrust element is a rotational valve and said rearward thrust element is a panel or vane or panel with vanes in combination with a fan.

22. The aircraft of claim 21 wherein said forward thrust element is a rotatable valve with at least two thrust delivery angles; wherein said rearward thrust element is a movable panel of a first size that comprises independently movable panels of a second size smaller than said first size; wherein said forward thrust element delivers gases from an internal area of said fuselage or said wing, wherein; said forward thrust element is a cylindrical element rotationally attached to said aircraft, said cylindrical element being rotatable to effect more than one thrust direction, said more than one thrust direction compared to said longitudinal axis; wherein at least one of said rearward thrust element and said forward thrust element expels exhaust gases derived from said prime mover; wherein said aircraft has a hollow portion within said aircraft, said prime mover residing within said hollow portion.

23. The aircraft of claim 10, wherein said rearward thrust element comprises a fan or propeller in combination with a series of flaps or variable vanes that direct gases downwardly, such that at least one first flap and at least one second flap direct gases downwardly at at least one first angle and at least one second angle different from said first angle.

24. The aircraft of claim 10, wherein said device comprises at least two prime mover elements rotating about an axis, said at least two prime mover elements comprising at least a first prime mover element and a second prime mover element, said first prime mover element cooperating with said second prime mover element to supplement a power of said second prime mover element, said first prime mover element and said second prime mover element rotating in opposite directions around said axis.

25. The aircraft of claim 10, wherein said aircraft comprises at least one prime mover in combination with a fan and at least said at least one exhaust deflector or said fan comprising means for thrust vectoring.

26. The aircraft of claim 10, wherein said aircraft further comprises a gaseous accumulation chamber, wherein energy from said gaseous accumulation chamber is effectively used for at least two purposes, the two purposes including at least: a first purpose including delivering power to said prime mover; a second purpose including delivering gases to a downward thrust element

27. The aircraft of claim 10 wherein said rearward thrust element is a variable angle vane or set of variable angle vanes placed behind, relative to said longitudinal direction, a fan or propeller, to deflect a gaseous flow delivered by said fan or propeller.

28. The aircraft of claim 10 wherein said forward thrust element is a rotatable valve with at least two thrust delivery angles; wherein said rearward thrust element is a movable panel of a first size that comprises independently movable panels of a second size smaller than said first size; wherein said forward thrust element delivers gases from an internal, constricted volume of said fuselage or said wing; wherein said forward thrust element is a cylindrical element rotationally attached to said aircraft, said cylindrical element being rotatable to effect more than one thrust direction, said more than one thrust direction compared to said longitudinal axis; wherein at least one of said rearward thrust element and said forward thrust element expels exhaust gases derived from said prime mover.

29. The aircraft of claim 10 wherein said prime mover is a flywheel comprising a rotational velocity and further comprising a compressor stage and a turbine stage within or unitary with said flywheel, said compressor stage and said turbine stage locked for rotation together such that said compressor stage and said turbine stage rotate at an equal rotational velocity, one to another; wherein said prime mover drives an auxiliary drive comprising a drive torque, and pressure from said accumulation chamber is rendered into electrical energy which supplements said drive torque.

30. The aircraft of claim 10 wherein said prime mover comprises a gaseous accumulation chamber that delivers pressurized exhaust gases from said prime mover to said forward thrust element.

31. The aircraft of claim 10 wherein said prime mover comprises a turbine and said gaseous accumulation chamber accumulates exhaust from said turbine, for expansion to effect a secondary thrust using said accumulated gases or a refeeding of power to said prime mover.

32. The aircraft of claim 10 wherein said prime mover is a flywheel comprising magnets and compressor vanes.

33. The aircraft of claim 10 wherein said prime mover is a flywheel comprising a rotational velocity and further comprising a compressor stage and a turbine stage within or unitary with said flywheel, said compressor stage and said turbine stage locked for rotation together such that said compressor stage and said turbine stage rotate at an equal rotational velocity, one to another.

34. The aircraft of claim 26 wherein said prime mover drives an auxiliary drive comprising a drive torque, and pressure from said gaseous accumulation chamber is rendered into electrical energy which supplements said drive torque.

35. The aircraft of claim 26 wherein said gaseous accumulator comprises an internal hollow space and within said internal hollow space resides at least one of: said prime mover; a fuel tank; a fuel injection system; a flywheel in combination with electrical elements configured to establish a regenerative braking scheme for said prime mover.

36. The aircraft of claim 10 wherein said prime mover is a hybrid turbine flywheel and said rearward thrust element is a fan deflector or propeller deflector and said forward thrust element is a turbine exhaust outlet comprising at least a closed state and a thrustor state.

37. The aircraft of claim 10 wherein said aircraft comprises a turbine, wherein said turbine emits an exhaust that communicates with at least one exhaust chamber, wherein an auxiliary expansion device derives supplemental energy from said turbine exhaust for a secondary purpose, said secondary purpose including one of aircraft thrust and prime mover velocity.

38. The aircraft of claim 10 wherein said aircraft comprises at least two turbines, at least two forward thrust elements, and at least two rearward thrust elements.

39. The aircraft of claim 38 wherein: said at least two rearward thrust elements reside on two separate wings of said aircraft.

40. The aircraft of claim 38 wherein: said exhaust gases from said at least two prime movers are selectively usable by at least two of said at least two turbines or said rearward thrust element or said forward thrust element or for thrust vectoring or energy sharing among turbines.

41. An airfoil comprising a substantially hollow interior and a longitudinal axis, said hollow interior comprising a turbine, said airfoil further comprising at least two multi-vector downward thrust elements, a first multi-vector downward thrust element residing forwardly of said turbine, forwardly being along said longitudinal axis, a second multi-vector downward thrust element residing rearwardly of said turbine, rearwardly being along said longitudinal axis and in an opposite direction from forwardly, wherein; at least one of said first multi-vector downward thrust element and said second multi-vector downward thrust element variably delivers thrust gases at more than one angle relative to said longitudinal axis, wherein; at least one of said first multi-vector downward thrust element and said second multi-vector downward thrust element variably delivers thrust gases from the exhaust of said turbine.

42. The airfoil of claim 41, further comprising a travel direction and said turbine providing an exhaust, said airfoil comprising a forward portion and a rearward portion in relation to said travel direction, said forward portion comprising a forward thrust element and said rearward portion comprising a rearward thrust element, wherein: said forward thrust element is at least one downwardly angled modulated valve or valves in fluid communication with an exhaust of said prime mover; said rearward thrust element is a rotationally or arcuately movable panel in combination with a fan or propeller, wherein; said prime mover passes gases to an accumulation chamber and at least one of said accumulation chamber and said fan or propeller is configured to direct gases at more than one downward direction relative to said travel direction.

43. The airfoil of claim 41, further comprising longitudinal axis, below said longitudinal axis is a downward direction and above said longitudinal axis is an upward direction, said airfoil further comprising a longitudinal direction, said longitudinal direction and said airfoil having a direction of travel in which a forward direction is substantially along said longitudinal axis and a rearward direction is in a direction substantially opposite to said forward direction, said airfoil comprising a fuselage or wing, said airfoil further comprising a prime mover, wherein; said airfoil comprises a forward portion and a rearward portion and comprises: a forwardly residing thrust element that delivers gases in a downward direction; forwardly corresponding to said forward direction along the longitudinal direction and downwardly being in said downward direction which is downward of the longitudinal direction; a rearwardly residing thrust element that delivers gases in a downward direction; wherein; at least one of said forward thrust element and said rearward thrust element is a variable angle gas delivery or gas deflection element that delivers or deflects gases downwardly of said longitudinal axis at a first angle and also at at least one second angle distinct from said first angle relative to said longitudinal axis.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0048] The foregoing discussion will be understood more readily from the following detailed description of the invention, when taken in conjunction with the accompanying drawings.

[0049] FIG. 1 is a flow diagram for the flow of gases through the various modules used to implement the present invention.

[0050] FIG. 2 is a semi-cross-section (cross section of one sector) of the turbine flywheel TF showing the compressor, turbine, stator, generator, and combustion modules.

[0051] FIG. 3 illustrates an embodiment of the reversible pump-motor PM1, the motor-generator MG, and the transmission between these and the drive axle of a vehicle.

[0052] FIG. 4 is a gas flow strategy for selectively changing the mode of expansion through the reversible pump motor.

[0053] FIG. 5 is a table explaining the six currently foreseen combinations of valve settings for FIG. 4.

[0054] FIG. 6 is a cross-section taken along line 6-6 of FIG. 9, showing the effective cross-section of the majority of the vehicle of the first embodiment of the invention.

[0055] FIG. 7 is a cross-section taken along line 7-7 of FIG. 9, showing the cross-section at the center of the vehicle of the first embodiment of the invention.

[0056] FIG. 8 is a cross-section taken along line 8-8 of FIG. 9, showing the cross-section at the side of the vehicle of the first embodiment of the invention.

[0057] FIG. 9 is a top cross-sectional view of the vehicle of the first embodiment of the invention, providing basis for FIGS. 6-8.

[0058] FIG. 10 is a rear elevational view of the vehicle of the first embodiment of the invention.

[0059] FIG. 11 is a table providing the chronology of steps utilized in hybrid operation of the first embodiment.

[0060] FIG. 12 is a table providing the chronology of steps utilized in transitioning to high-consumer mode from hybrid mode, and also for transitioning back to hybrid mode, or a parked configuration, from the high-consumer mode.

[0061] FIG. 13 is a continuation of FIG. 12.

[0062] FIG. 14 is a view of a rotor vane of the axial compressor shown in FIG. 2.

[0063] FIG. 15 is a cross-section taken along line 15-15 of FIG. 14, showing the magnetic core of the rotor vane of the axial compressor.

[0064] FIG. 16 is a close-up of area A of FIG. 2 showing the bias seals of the turbine flywheel module.

[0065] FIG. 17 is a top or bottom view of a VTOL aircraft of a second embodiment of the invention.

[0066] FIG. 18 is a cross-section taken along line 18-18 of FIG. 19, showing the in-wing orientation of the parts in the second embodiment of the invention.

[0067] FIG. 19 is an elevational view from above the wing of the aircraft of the second embodiment of the invention, showing the fan, wing, ailerons, and VTO flaps of the second embodiment of the invention.

[0068] FIG. 20 is a view of the casing of the turbine flywheel and the gas transmission passage of the second embodiment.

[0069] FIG. 21 is a top cross-section of the combustor of the turbine flywheel.

[0070] FIG. 22 is a bottom view of the turbine flywheel showing the spacing of the combustors around the turbine flywheel.

[0071] FIG. 23 is a schematic of the gas flow for a first mode of operation of the second embodiment.

[0072] FIG. 24 is a schematic of the gas flow for a second mode of operation of the second embodiment.

[0073] FIG. 25 is a schematic of the gas flow for a third mode of operation of the second embodiment.

[0074] FIG. 26 is a side view of s vehicle utilized in implementing a third embodiment of the invention.

[0075] FIG. 27 is a rear elevational view of the vehicle utilized in implementing a third embodiment of the invention.

[0076] FIG. 28 is a side view of the vehicle utilized in implementing a third embodiment of the invention towing another vehicle.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0077] The following description of FIG. 1 is meant to be understood in conjunction with FIG. 2. The flow chart of FIG. 1 shows the flow of gases through the entire system. Air enters the system from air intake 1 and passes, via a shutter valve (described later) after traversing a heat exchanger (described later) to the first compressor group 2. The air is compressed by first compressor group 2, which is driven by the second turbine group 5 and is integral with the first generator/flywheel 6. The air passes from the first compressor group 2 to the second compressor group 3, which is driven by the first turbine group 1 and is integral with the second generator/flywheel 7. In the embodiments of the present application, 2, 5, and 6 are concentrically arranged about a longitudinal axis 50, and 4, 3, and 7 are also concentrically arranged about said longitudinal axis 50. After the second compressor group 3, the compressed air enters a combustor C, which for this discussion can be seen as a typical combustor can but which will later in the application be discussed further a propos of its geometry when applied to the TF. The exhaust from the combustor passes to the first turbine group 4 and then, after traversing a recuperator R, to the second turbine group 5. The exhaust passing from the second turbine group enters, via a shutter valve (described later), a pressure accumulator PA1.

[0078] The pressure accumulator can be large and in the embodiments of the present application it surrounds the greater part of the TF casing and is confined by the outer walls of a vehicle. The pressure accumulator PA1 communicates with the ambient air outside of the vehicle via a reversible pump/motor PM1 and possibly other pump/motors 12, which when driven by air expanding therethrough are motors, usually driving a motor/generator (in the case of PM1, it drives MG1), and when taking air into the pressure accumulator PA1 to charge it to higher pressures, are driven by the motor/generator and act as pumps. Further escape valves allow gases within the pressure accumulator to pass directly to the environment, as shown by passageways a, b, and c leading from the pressure accumulator PA1 to outside 13. Shaft 11 depicts the rotational interlock between the reversible pump/motor PM1 and the motor/generator. Motor/generator MG1 is electrically connected to a DC bus 15, which communicates with first and second generator/flywheels 6 and 7. The DC bus is further connected to the load L, which could be in-wheel electric motors with regenerative breaking reversing the electrical flow back to the bus from the load. The DC bus is also connected to auxiliary systems, the cabin, and possibly (in embodiments not of interest in the present application) a battery and/or docking station. An evacuation pump 8 is connected to the combustor C, preferably near the air inlets or near the burner nozzle, possibly in conjunction with the latter, and when activated causes a negative pressure which removes any air in the combustor. This will be described later.

[0079] The air from the evacuation pump also passes out to ambient 9. Reference numeral 10 indicates a further provision, not dealt with in the present application, whereby instead of expanding the gases through PM1, or in addition thereto, the gases in the accumulator are passed through the first and second turbine groups 4, 5, again, without combustion, to ambient. This provision is not at this time seen as fruitful, but has been included for the sake of full disclosure.

[0080] Turning now fully to FIG. 2, although reference may be made to FIG. 1 throughout the disclosure, the air entering the inlet 20 is shown as airstream 22. After the inlet 20 it enters a centrifugal compressor C1, which in this embodiment makes up the entirety of the first compressor group 2. The air passes outwardly along compressor C1, being thereby pressurized and flung into volute V1, where it may be guided by diffuser D1 and/or stator vanes, swirl vanes, anti-swirl vanes, etc. into the first stage (C2 and S1) of the second compressor group 7. The compressor C1 is attached to, and locked for rotation with the second turbine group 5, namely the fourth turbine stage T4 which is a centrifugal turbine. The compressor itself is, and in this case the vanes between the air passages are, embedded with magnetic elements M near the casing 21 and preferably as far to the radially outer extreme of the compressor as possible. The magnetic elements interact with conductive coils i in or on the casing to create or absorb electrical current. The magnetic elements M plus the conductive coils i make up the first flywheel/generator 6, in that the mass of the magnets plus the combined masses of the compressor and turbine carry a rotational inertia about 50 which resists the voltage acting against its continued rotation during electrical current creation. Further, when an EMF is applied across i, the magnetic elements M are accelerated in a direction depending upon the direction of the current.

[0081] As stated, the air passes from the first volute V1 and into the first compressor stage C2 and S1. C2-C7 are axial-compressor rotor vanes and each has a root 23 that sits in and is anchored by, in a preferred embodiment, layers of fiber-reinforced plastic or carbon-fiber-epoxy sheets that have been spun around the rotor wall 25, with the roots temporarily attached, and cured, permanently and durably fastening the compressor vanes C2-C7 to the rotor wall. The strength of this bond is important as the system will rotate at extremely high velocities. The stator vanes S1-S5 are traditional stator vanes and are interspersed with the compressor vanes C2-C7. Each compressor vane C2-C7 is embedded with a magnetic element M which interacts with conductive coils i in the same way as described in the preceding paragraph. The magnetic elements M, the fiber/resin layers 24, and the bodies of the compressor vanes C2-C7 make up the greater part of the mass of the rotor of the second compressor group, and thus form a flywheel as do corresponding elements of the first compressor group 2, and by much of those items being magnetic, also form a generator. It is here noted that 30 indicates an annular disk with solid, structural elements 26 and 29, and passageways S6, C8, C9, and T3. The gases exiting the last turbine stage pass through stator S6 and then to a passage, also vaned, to turn and pass through a stator C8, which is here labeled as a compressor stage C8 because the air, being entrained within the body of rotor 28, 25, 42, 45 etc. at this point, will see the stator C8 as a compressive stage C8, and will be further compressed such that when it passes to rotating passage 45, it seems stationary in the relative frame of the rotor as if it had just passed through a single compressor stage. Now arrived at passage 45, said air passes leftward, as seen in FIGS. 2, and 45 becomes a manifold whereby an annular passageway 45 is divided into dozens of sector-shaped passages 47 interspersed with sector-shaped passages 48 which carry exhaust that is downstream of the combustor. This is the recuperator R, whereby the thin walls separating 47 and 48 (the dotted lines for 48 indicate that the cross-section used for FIG. 2 is in the plane of the compressor side sectors 47, which are shown with solid lines) pass heat from the combustor-downstream sectors 48 to the air in the air currently under discussion, raising its temperature and thus, performing work on it and taking work from the turbine side.

[0082] The air enters another manifold where it merges back into an annular passageway and enters another stator C9, which for the same reasons given for C8 is treated as a compressor stage. The edges of the entry and exit vanes of 45 and 53 should be bent to an angle to complement such a relationship with the stator vanes C8 and C9, as should the edges of passageways 40, 41, and 44. The air now enters a passageway 40 where it is again flung outwardly (this could be seen as a compressive stage but the air therein is only regaining the energy it lost by being pushed toward the axis 50 in 27 and R to begin with, so this will not be discussed). The air enters a stator S7 where it is deflected to a proper exit angle to act on C10, which with C11 make up the final two compressor stages 39, separated by another stator S8. By the time the air enters the combustor C through passage 33, it will have been acted upon by approximately 11 compressor stages, one of which is a large centrifugal compressor, such that with the recuperator R the enthalpic rise should be the equivalent of at least a 14-stage axial compressor. It is mentioned in passing that the recuperator and change-of-direction passageways can be done without and the air could simply pass from S6 to 33. The more complicated embodiment has been included for patent purposes for it inherently comprises all the elements of the simpler ones. 31 depicts the outer edge of rotor segment 42. The rotor has been divided up into segments 2, 48, 47, and 46 to show that during manufacture it can be stacked and that it would not be required to perform the impossible, which would be to have the rotor formed whole. In the event that 30, the turning passages, and the recuperator R were removed from the concept, these considerations would be less profound. It is also envisioned that annular segment 30 could extend all the way to axis 50 and 42 would be a third compressor/turbine/generator/flywheel rotating independently of 2/5/6 and 3/4/7, but in this case it is uncertain at this time what turbine would drive compressor stages C2-C7.

[0083] Continuing with the discussion of the rotor depicted by reference numerals 42, 28, and 31, more magnetic elements are spaced around the periphery near 31 and interact with conductive coils i, as previously described. 28 and 42 are not actually solid, but insofar as the air is concerned, they are. The air enters the combustor at 33 where it passes into the combustion chamber through nozzles 34 and it is ignited by a fuel mix coming from fuel burner nozzle 32. 35 are flame propagation nozzles that contribute to forming the flame and preventing the flame from passing upstream. This is well known in the art. The exhaust of the combustor passes through 36 to impinge on first turbine stage T1 which in this embodiment is of a piece with C11, as is S9 with S8, T2 with C10, and S10 with S7. This arrangement is hoped to save space and allow the radial compressor stages and turbine stages to coexist and be advantageously located radially inwardly of the combustor and at the end of the machine. Wall 37, with 21, completes the outer casing of the device.

[0084] The stators 38 of the first two turbine stages could easily be made to swivel via a simple ring gear to be variable stator vanes, allowing it to change the flow characteristics through the first turbine group 4 to adjust for different altitudes and rates of combustion. The air passes from first turbine group 4 to another passageway 41 which delivers it to another stator T3 which for the same reasons as C8 and C9, is being treated as a turbine stage. Although counterintuitive and hard to understand, the laws of gas turbine engine theory can be used to prove that energy is recovered from the exhaust stream here (as it is provided by C8 and C9), and although it is not the intention of the present application to define this, the inventor sees this as far simpler than describing how it is actually 27, 45, 40, 41, etc. that are absorbing and performing the work. The virtual enthalpic ratio across T3 can be seen as approximately 1.4:1, and the same goes for C8 and C9. From T3 the exhaust enters another manifold 44 which splices with manifold 43 to create the sectored recuperator R described above. Element 49 exists in the compression side 58 of sectors 47 and is used to guide the flow from 45 to 43, bringing it out in an opposite axial direction from how it entered. However, no such element is used in the turbine side sectors 47 because the air from T3 moves more or less axially to arrive at another manifold, also indicated as 44, to be fed into the second volute, V2. It is noted at this time that V1 and V2, as well as any space or substance between them, are part of an annular body 57 that is fixed to the casing 21 and extends radially inwardly therefrom. Like V1, volute V2 can also have a diffuser D2 or some type of swirling or anti-swirling vanes, and is integrally vaned to evince some type of indescribable, despite conceived efforts, stator vane which serves as a volute for the fourth and final turbine stage, T4, which is the sole representative, in the preferred embodiment, of the second turbine group 5. T4 and C1 are locked for rotation with each other and sit on a spindle 52, which nests around shaft 53 which is integral with the rotor 42, 46, etc. at 51. Spindle is separated from the main rotor 42, 53, etc. by bearings B to define a space 45. It is unknown at this time what type of bearings would be most cost-effective, but of course the idyllic embodiment would be levitational-bearings (alternating magnetic fields facing each other creating constant repulsion). 54 defines the output shaft and is integral, in the preferred embodiment, with 42, 53, etc. The overall machine is quite small, so it is not unforeseen that 54 could be cast or forged with 42. The air exiting T4 passes to outlet.

[0085] In operation, 5 drives 2 and 6, and 4 drives 7 and 3. Any force on 5 will be communicated to 2 and 6, any force on 2 will be communicated to 5 and 6, etc. Any force on 4 will be communicated to 7 and 3, etc. This is why 5, 2, and 6 are shown in FIG. 1 to be on a virtual shaft, although there is no shaft, they are integral. The same goes for 4, 7, and 3. This is why the device is called an integral gas turbine, flywheel, and generator.

[0086] It is noted that to ease understanding of the invention, one would be well advised to skip the discussions of FIGS. 3-5 and return to them only when a fuller understanding of the overarching concepts has been established. They are not directly claimed in the present application. However, for disclosure and best-mode purposes, as well as to provide basis for being claimed in later applications, it is necessary to describe them now.

[0087] FIG. 3 shows pump/motor PM1 and motor/generator MG1. Air enters this system from PA1 via 76 and immediately encounters a three-way, three-position valve that serves to close PM1, send gases to a turbine 82 via path 79, or bypass the turbine and, along path 78, send gases directly to the piston cylinders 70-72 that make up the vital portion 73 of PM1. The air entering the turbine enters through a standard volute V3 and exits at 81. After 81 the air enters a distributor 75 that is actually represented by FIG. 4 and is not simply an entrance manifold. 70-72 become progressively larger and the air is successively expanded, after (or not) being expanded in the turbine, through these three stages, and harnessed for work thereby. The piston rods 74 turn a crankshaft 83 at 80, on which is also disposed the turbine 82 and the mechanism by which the turbine powers the crankshaft. Extending from turbine 82 is a stub which is notched all the way around to make a sun gear 84. Around the sun gear are orbital or planetary gears 89 that engage the teeth of the sun gear and rotate on planet carrier 85 which can be braked by 87. The output of the planetary gears is passed along to the ring gear 86 which is fixed to the crankshaft 83. This type of gear reduction is well known in the art and needs not be defined here, save to state that braking and de-braking the carrier 85 leads to two different step-down ratios, such that the turbine should be able to drive the shaft over two distinct or overlapping ranges of pressurization upstream of the turbine. At these (relatively higher) PA1 pressures, the exhaust from turbine 82 passes to 75. At lower PA1 pressures the turbine becomes useless and 77 is switched to path 78. Regardless of whether the turbine has bee cut in or out at 77, the exhaust now expands in 70, 71, and 71. At relatively higher pressures it may be advantageous to expand the exhaust through 70-72 in succession, and that is why 72 is shown as larger than 71, 71 is shown larger than 70, etc. However, after drawing FIGS. 3 and 4 the inventor, upon weighing both alternatives, believes that the best embodiment for PM1 would be to pass the exhaust through all of the piston-cylinders in parallel and forego the turbine during hybrid operation (described later). Exhaust would simply be valved in on the pressure side of the cylinder at a pressure slightly above the ambient pressure (the outlets of the piston-cylinder arrangement communicate with ambient air). The control of this valving will be of vital importance, for if done properly the pressure drop across the cylinder can be kept as low as possible, and the movement of the piston rods as slow as possible, maximizing the energy rendered.

[0088] The driven parts 74 and 86 drive the crankshaft which, on the left end, is surrounded by a sleeve 93 which is further surrounded, at two points, by outer sleeves 94 and 104. Outer sleeve 104 can be clutched to crankshaft 83 by clutch 103, locking the rotor 105 of the motor/generator MG1 for rotation with the crankshaft. Clutch 102 locks 105 for rotation with sleeve 93, which is clutched, via a direction-reversing arrangement, to an output pulley 96, which with belt 107 and axle pulley 108, comprise a continuously variable transmission (CVT) of known type. The outer periphery of sleeve 94 is splined and carries, on each side of output pulley 96, sun gears that cooperate with planetary systems 92 and 97, one of which has a single ring of planet gears and the other has a double ring of planet gears, such that the ring gears 99 and 91 will be driven in opposite directions from each other, inverting the drive relationship between 107 and 83 depending on whether clutch 91 locks 100 for rotation to sleeve 93 or clutch 101 locks 100 for rotation with sleeve 93. Clutch 90 locks the sleeve 93 for rotation with crankshaft 83. It will be apparent to one skilled in the art that the piston rods 74 can drive MG1 without connecting to the CVT, the CVT can drive MG1 (or vice versa) without connecting to the piston rods or the turbine 82, and the piston rods and/or turbine can drive the CVT (or vice versa) without connecting to MG1. 109 is a service brake and will be used when loading the axle 88 via PM1 and MG1 is insufficient for achieving the desired braking force. 106 is the stator coil of the motor/generator MG1 and its polarity will be oscillated and inverted to energize or be energized by the rotor 104.

[0089] FIGS. 4 and 5 describe how the air from PA1 can be sent to the expansion modules 70, 71, 72, and 82 in different modes of operation. Theory will be foregone at this point and the parts described. The device works as shown in FIG. 5 and only a description of the parts will be made here. 77 is the same three-way valve from FIG. 3, cutting in or out the turbine 82. A check valve 120 is provided in outlet 81 of turbine 82 to prevent backflow. Before valve 124, line 78 splits off on line 121 to enter the inlet 125 of piston cylinder 70. Switch 122 inverts the relationship between inlet 125 and outlet 126, such that first one side (top) of 70 is the pressure side, and then when the piston has traversed the cylinder, that side (top) becomes the relief side. The return line 123 enters valve 124 in parallel with line 78. Valve 124 switches the feed from lines 78 and 123 to lines 127 and 131 as shown by the arrows associated with a and b. 128, 129, and 130 are exactly the same as 121, 123, and 122, respectively. Valve 132 can only be described by directing a reader to the arrows of a, b, and c and allowing them to be imagined in each of their three settings as relates to lines 133 and 134. These types of valves are known in the art and would unduly encumber the disclosure if an attempt were to be made to describe them. In short, the air arriving from 137 can arrive there after being passed through the cylinders and turbine according to the modes 140-145 in FIG. 5, each being a combination of valve settings which cause series or parallel or hybrid series-parallel flow through the piston-cylinders, depending on the pressure within PA1 and the power output requirements of PM1, as well as external concerns.

[0090] FIGS. 6-8 correspond to FIG. 9, which shows a vehicle according to the first embodiment of the invention as if the top were removed revealing the internals. TF is the turbine/flywheel of FIG. 2, and MG1 and PM1 are the same as those from FIGS. 1 and 3. Turning first to FIG. 9, the body of the vehicle is shown as 238. Seats 227 are provided for passengers in the event that this is a passenger vehicle. An electric motor 251 is provided, now taking the place of the load L, for each of the rear wheels and communicates with the electrical bus of FIG. 1. A cowl 212 encases a fan or propeller 210. Wheels 234 are steering wheels and are connected to the drive axle 88 and, thereby, to PM1 and MG1. Pitch/roll/yaw stabilization nozzle housings 239 are on the front corners of the vehicle, and vertically sweeping radar modules 241 are provided to sense the orientation of obstacles and terrain relative to both front corners of the vehicle. 232 is a camera to provide a dash display of the field of view that the driver cannot see, more or less that below and before the vehicle. 201 is an intake manifold for the turbine/flywheel TF, and 206 is a plate heat exchanger for the TF's exhaust to thermally communicate with its intake. 209 is the drive shaft for the fan and it can directly couple to the output shaft 54 of the TF. Lines 6-6, 7-7, and 8-8 relate to the cross-sectional cutaway FIGS. 6-8, respectively, and show approximately where FIGS. 6-8 pertain across the lateral extent of the vehicle.

[0091] Turning to FIG. 6, the dotted line 229 surrounding the vehicle is included to show that the major expanse of the vehicle's body 230 conforms to the shape, as nearly as possible, of an ideal airfoil. The flap 225 folds up, to spoil this shape and cancel lift, and down; to complete this shape such that, given sufficient thrust and pitch/yaw/roll stabilization, the vehicle will automatically become airborne. PA1 commandeers every cubic inch of the vehicle not needed for personal use. The larger it is, the more gas it can store, the more efficient the system becomes. 224 is the back wall of the vehicle and holds 226, which is the hinge upon which flap 225 pivots. 231 is a fuel tank. 233 is the dash and control module of the vehicle, and 228 is hoped to show the creation of leg-room for occupants of the vehicle. All ergonomic considerations cannot be dealt with in this application, and therefore have been mostly omitted.

[0092] FIG. 8 shows what the vehicle of the first embodiment might look like from the side. It does not look like an airfoil because of panel 237, and it is assumed that this will be pleasing to a customer, that his/her car not look outlandish. 225 is shown in its upright configuration, and a spoiler fin 235 shows other aspects that might be added for aesthetic purposes, as well as to offer a moment to expound on other features that might be desirable. Such as, although no one wants wings on their car, it might prove optimal to locate other airfoil-shaped objects around the vehicle to supplement lift and stability. Also, from the spoiler shown a tail-fin might be made to pop up, providing a good location to implement a rudder. It is doubtful the vehicle would be stable without a rudder. Dashed line 236 indicates the location of back wall 224 on the other side of panel 237. 238 is meant to be the main body of the cabin, comprising doors, roof, etc. Pitch/yaw/roll stabilization nozzle housings each have three nozzles 140, selectively actuated, allowing bursts of gas to escape PA1 upwardly, downwardly, and laterally outwardly, from each corner of the vehicle. It is believed that with no great amount of computing power, a 6 D.O.F. accelerometer/gyrometer and the proper algorithm, unwarranted pitching, yawing, and rolling can be offset and smooth air travel experienced. In all of FIGS. 6-8, 221 represents the inhabitable space of the interior of the vehicle.

[0093] FIG. 7 shows the preferred embodiment for implementing the system of FIG. 1. Air is taken in at the inlet 201 and passes through plate heat exchanger 206 where it experiences thermal exchange with the exhaust from the TF, which is forced down into PA1 by 202 and is shown as arrow 203 coming out of the heat exchanger into the pressure accumulator. From 206 the air enters the TF via a manifold 219, which takes the concentrically arranged inlet and outlet streams from the TF and places them in alternating passages, making heat exchange more efficient and simplifying the device 20, which is a seal, having two positions, and by sliding it up and down the controller can close simultaneously the inlet and outlet of the TF, or simultaneously open them. 70 and 71 are shown to represent the piston-cylinder array 73 of PM1 and 108 is the drive pulley on the drive axle, 107 being the belt of the CVT. 204 is a thrust reverser for the intake air, and can be opened while 201 is closed to take in air vertically instead of horizontally.

[0094] A vertical take-of valve VTOV is provided to send air, through bore 205, through outlets A, B, and C. By controlling it, gases from PA1 escape therefrom at high velocities, modifying the thrust vector of the vehicle overall. Passage A sends the gases rearwardly where they escape at 216 and supplement thrust of the fan. 217 is a panel with outlets which can be opened such that air 218 is directed downward, in the event this device is to be used as a hovercraft or hydrofoil. Although this is foreseen, it is not a subject of the present application. Position B directs gases directly downwardly. Position C directs gases downwardly and forwardly, also acting as a thrust reverser to be used with 204 in certain applications.

[0095] The right-hand side of FIG. 7 depicts a vertical take-off module comprising manipulable flaps 213, flap panel 215 having tracks for the flaps 213, and the fan casing 212 and hub 211. Airstreams are shown to portray how each of the panels in its different position affects the air through and out of the turbine. Vertical panels 214 pop up from the flap panel 215 when it is fully extended and before the flaps 213 are moved up. These panels 214 serve as outlet guide vanes for the turbine and disallow stream migration and surge when the flaps are in different positions from each other. A rotational shaft-to-shaft coupling 208 allows connection of the TF to the drive shaft 209 to drive the fan. The output shaft 54 of the TF is as short as possible. It possesses trunnions or splines that mate with corresponding female members on the inside of a sleeve or collar that can be slid, in the direction of the arrow shown by 208, over the output shaft, such that the trunnions or splines drive the collar or sleeve, which in turn drives, through reduction gearing similar to that shown in FIG. 3, the drive shaft and thence the fan.

[0096] FIG. 10 shows a rear view of the components of FIGS. 6-9 and will not be explained again except in those reference numerals that were not explained above. Namely, that the flaps 213 can assume any imaginable combination of angles, such as a controller might deem appropriate for vector nozzling the fan thrust. Also, that 223 dips down farther than 224 by the inlet of the fan, but no more than necessary. Also, that ailerons 242 have been considered but it is unknown at this time whether they will be necessary, due to item 239. However, in the event that they were desirable, they would pivot as shown by arrow 243. FIG. 10 has been included to exhibit the extent to which the airfoil shape can be effected while preserving an unobjectionable shape for the overall vehicle.

[0097] FIG. 11 is exactly what its title says. This is how the system will operate from origin to destination, in normal day-to-day ground travel. The steps have been listed here for disclosure purposes. It is noted with emphasis that the last step of the method charges the PA1 and seals it off, such that when an operator starts the vehicle again, the first can be performed.

[0098] 1.) Start-up: [0099] Depressurize pressure-accumulator PA1 through reversible pump-motor PM1. [0100] Route generated electricity from PM1 to conductive coils (i), accelerating TF. [0101] Open inlet and outlet of TF. [0102] Commence combustion in combustor C.

[0103] 2.) Run-up and Hybrid Operation with P>Pmin: [0104] Combust until 1 (TF rotational velocity 1) and P1 are reached (load can be energized at this time) [0105] When P=P1, close inlet and outlet of TF. [0106] Compressors and turbines self-evacuate with assistance from pump and relieved (open) bias-seals. [0107] Slowly expand gases in PA1 through PM1 (currently a motor-generator), electrically accelerating TF. [0108] Deceleration of TF via energization of Load L. [0109] Acceleration of TF via braking of Load L. [0110] Successive reiteration of steps 2-5 and 2-6 until P=Pmin (or insufficient upcoming brakings foreseen). [0111] Meanwhile, during quick-stops (brake-force required larger than reverse load capacity of load L): Reverse PM1 (now a pump), utilizing supplemental brake-force to draw ambient air into PA (Supplemental braking requirements excessive) Activate service brake. [0112] When P=Pmin OR 1=1min (or insufficient upcoming brakings foreseen)go to step 1-3.

[0113] 3.) Shutdown/parking: [0114] Close (if open) inlet and outlet of TF. [0115] Route electrical energy from TF to PM1. [0116] Reverse PM1 to pump ambient air into PA. [0117] When 1=0, close PM1resulting in hermetically sealed PA with sufficient charge to begin step 1.

[0118] FIGS. 12 and 13 get a little more involved, but again there is no need to explain an explanation. The best way to understand the first embodiment is to mentally trace these steps (above and below) and although these are special cases of usage, they fulfill the inventor's obligations of best mode, enablement, and industrial applicability. Each routine, as in scenarios 1-3 above, is best described by its heading.

[0119] 4.) Starting from road travel with moderate at decision moment (i.e. typical highway lift-off): [0120] Close (if open) PM1, sealing PA1 (vertical take-off valve VTOV already closed). [0121] Open (if not already open) inlet and outlet of TF and commence combustion (if not already combusting). [0122] While P increases to Pmax, direct all electrical energy from TF to load L, accelerating vehicle. [0123] When P=Pmax, cease combustion, close inlet and outlet of TF, open fan F inlet and flap panel to idle fan. [0124] Electrically transfer all kinetic (rotational) energy from TF module 1 (TFM1) to TF module 2 (TFM2) and L. [0125] When TFM1 and F are rotationally matched (via reduction gearing ratio), slide collar over trunnion. [0126] Open PM1 to maximum throughput, transfer all energy from PM1 and TFM2 to TFM1 and L (until/unless vehicle velocity is near lift-off velocity, then deactivate L for duration of flight) [0127] Open inlet and outlet to TF, commence combustion, positively drive F at lift-off thrust [0128] Although PM1 is still at max throughput, P will quickly reach Pmax). [0129] Selectively open vertical take-off valve VTOV to position A to complement fan thrust and to waste-gate PM1. [0130] If advantageous, momentarily (or for duration of lift-off) rotate VTOV partially/fully to position B and vertical take-off flap VTOF partially/fully upright to achieve pop up effect.

[0131] 5.) Starting from road travel with excessive at decision moment (i.e. atypical highway lift-off): [0132] Reverse PM1 (now a pump) and slow TF electrically via PM1 and L, charging PA1 and accelerating vehicle. [0133] When possible, open inlet and outlet of TF without combustion, further charging PA1 and slowing TF. [0134] When falls to predetermined rate, commence combustion; [0135] Go to step 4-3.

[0136] 6.) VTO with moderate (i.e. heliopad/driveway lift-off): [0137] Down flap panel, open fan inlet, open inlet and outlet of TF, commence combustion, charging PA1. [0138] Direct some electrical energy from TF to reversed PM1 (now a pump), further charging PA1. [0139] When P=Pmax, cease combustion, close inlet and outlet of TF, close PM1. [0140] Electrically transfer all kinetic (rotational) energy from TF module 1 (TFM1) to TF module 2 (TFM2) and L. [0141] Service brake applied (connect to front axle, PM1 pistons connect to generator) anytime prior to step 6-7. [0142] When TFM1 is completely stopped, slide collar over trunnion, raise VTOFs to near-upright (fan nozzled down). [0143] Open inlet and outlet to TF, commence combustion, continue to reverse PM1 via electricity from TF. [0144] When P=Pvto, quickly cycle VTOV to position C and switch to thrust reverser on front inlet. [0145] One VTOF has been left horizontal to keep down-thrust just shy of lift-off. It is now raised parallel to the others.

[0146] 7.) VTO with high (i.e. traffic lift-off): [0147] Reverse PM1 (now a pump) and slow TF electrically via PM1, charging PA1. [0148] When falls to predetermined rate, go to step 6-1.

[0149] 8.) Pre-planned or taxi-to-runway flight (since significant fuel is consumed by VTO, this may be common): [0150] Perform steps 1-1 through 2-7 until on straightaway/runway, then perform steps 4-1 through 4-11. [0151] With (GPS) knowledge of route (user's home and favorite lift-off), the computer can optimize fuel usage.

[0152] 9.) Road landing: [0153] Obtain altitude and alignment just above roadway, level out and run TF and F at cruise. [0154] Raise the central VTOF, or two outermost VTOFs, partway, to partially vector the thrust down [0155] Simultaneously with 9-2, cycle VTOV to position B. [0156] Loss of thrust in 9-2 and 9-3 reduces lift. Vehicle descends onto air cushion created by downward thrust. [0157] Several inches above roadway, level VTOFs and retract (toward fan) flap panel. Rear wheels touch down. [0158] A moment behind step 9-5, cycle VTOV closed and cease combustion. Front wheels touch down. [0159] Slide collar off trunnion, close fan inlet. [0160] Braking load drives TF to high w, go to step 2-5. [0161] (it is uncertain at this time when, whether, and how PM1 should be utilized during this procedure)

[0162] 10.) Vertical landing: [0163] Obtain approach position, attitude, and altitude. [0164] Cycle VTOV to position B and all VTOF's to max upright position, vectoring all thrust and exhaust downward. [0165] Pitch/roll/yaw nozzles PRYNs and TF driven selectively to stabilize speed, lift, pitch, roll, and yaw [0166] Vehicle coasts through a deceleration and descent curve to arrive mostly slowed, above and just shy of LZ. [0167] Cycle VTOV to position C and switch to thrust reverser on front inlet, bring horizontal velocity to zero above LZ. [0168] Attenuate fuel-in until touchdown. [0169] Slide collar off trunnion, close VTOV, retract (toward fan) flap panel, close fan inlet. [0170] Go to either step 2-1 (to taxi or drive) or step 3-1 (to park).

[0171] 11.) Other features: [0172] With GPS device, system can begin shedding energy a certain distance from one's destination. [0173] Docking station plug-ins allow vehicle to depart with maximum w and P, such that lift-off happens fully fueled.

[0174] Although the method is extremely complicated, it is believed by the inventor that with the capabilities of modern computers, a simple device with very few moving parts and a complicated control method is preferable to an inordinately complicated device (think vertically thrusting fan geared to main drive shaft) with a simple control method. Some compromise must be made in pursuing vertical take-off and landing, and the inventor believes he has not put forth more requirements on the controller than a modern lap-top computer could handle.

[0175] Continuing now to some essential attributes of the TF that were not mentioned earlier. FIG. 14 shows a typical axial-flow compressor vane. It is believed that no special shape will be needed for implementing the TF, however, as shown in FIG. 15, the inventor believes the preferred embodiment and best mode at this time are represented by a magnetic core 62 encased in the vane 63. U.S. Pat. No. 5,179,872 to Pernice provides for a magneto rotor having magnetic elements in pockets and the method of Pernice seems to be the best mode for achieving a workable model of FIG. 15. 62 would be an alloy of 33%-64% Nd/Fe (neodymium/iron) encased in, sintered in, or otherwise retained in aluminum vane 63. It is likely that the vast majority of TF will be of aluminum. As for the conductive coils in the casing of the TF, there are many ways to do this, and such is not the subject of the invention. What is important is that it be modified from encompassing the magneto or dynamo, as is usual in the art, and the loops tightened and multiplied to account for so many magnets. It goes without saying that in every aspect of this embodiment, the lightest materials are preferable.

[0176] FIG. 16 shows a feature necessary for sealing air passages from nearby air passages within the TF. When combustion is stopped, typical seals would create friction, slowing the rotors and being a detriment to the flywheeling thereof. Therefore seals 60 (they are all over FIG. 2 but not shown, as they are small) are strategically place such that when combustion ceases and the pressures inside the system diminish, the seals disengage from their land. They would be biased away from the land like a Belleville washer spring and the high pressures during combustion would close them. This requires that an analysis be made of the pressures throughout the system, such that the seal always face the right direction. Once properly placed, it is inherent that once combustion ceases, the seals would open and, all gases would migrate from areas of high pressure to areas of low pressure, and almost all flow in radial passages should be outward. That way, the entire system can be evacuated by draining the combustor with evacuation pump 8.

[0177] FIG. 17 shows the environment within which could be implemented through a second embodiment of the invention. The method is different and there are no magnets, but much of the rest of the system is the same. The concepts of the first invention have been extrapolated and modified to create an airplane capable of vertical take-off and landing. Aircraft 300 has within its wings 301 compartments 302a-c (and 302d-f in the other wing, not labeled). The compartments or chambers are separated by walls 303, 304 which might or might not have an opening for unobstructed migration of air between compartments. Gas turbine engine 305 is no longer called a TF and will be treated like any other gas turbine engine. Again, 70-72 are piston-cylinders that drive, like in PM1, a drive arrangement 306. Flaps and ailerons and panels 213-215 correspond to those in the first embodiment.

[0178] FIG. 18 is a cross-section taken along the wing 301 of the aircraft 300. Intake 301 passes air to the gas turbine engine 305. For simplicity, the gas turbine engine of FIG. 2 will be assumed to be within the housing of 305, except now it sits upright on a vertical shaft 331 (this was the embodiment originally designed for embodiment 1, as evinced by the provisional application, but the bevel-gears and entailing mass were thought to be of diminishing returns, however it would spin like a top). An outlet 303 leads either to a simple outlet diffuser 302 which results in the exhaust pressurizing the wing, like the pressure accumulator of the first embodiment. At 308 air enters a series of piston-cylinders 325 either in series or parallel, as explained before, and with an outlet at 324. The piston rods 326 turn a crank within 327 which turns bevel gear which drives bevel gear 305 which is fixed for rotation on the main shaft 307. Main shaft 307 is also driven by a bevel gear 304 which is driven by a toothed annular strip 329 on top of the first compressor stage. The vertical take-off nozzle 339 passes air selectively from inside the wing, through bore 340 to outlets 336, 337, and 338. These correspond to positions A-C of the first embodiment. A hydraulic pump 334 drives through a reversing valve 335, a hydraulic system that drives inner shaft 311 telescopically inside outer shaft 307. The inner shaft 311 has seals 310 which allow it to act like a piston inside the outer shaft 307. The inner shaft is threaded and knobbed at the end, the threads being shown at 312. The fan cowl 315 has an implement 314 atop it for cooperating with the inner shaft 311 to open and close the fan. Dashed line 322 shows the fan cowling in its dropped position. This is a non-use position for the fan. VTO flaps 316 and flap panel 317, as well as ailerons 318, perform as described in the prior embodiment 319 is the exhaust from the piston-cylinders. 320 is the hinge for the ailerons and 321 is the hinge for the flap panel.

[0179] FIG. 18 begins to make sense when viewed in conjunction with FIG. 19. FIG. 19 shows the top of the wing, the niche 355 for accepting the cowling in the non-use position, the hinge 354 for the cowling, the fan 349, and flaps 353 in their non-VTO orientations. 346 shows that the cowling is not just a box but really, all the way around, hollow with strut-vanes that direct air and support the fan. 347 and 348 are directed to the aforementioned scheme of using the telescoping shaft to hide or expose the fan. 347 is a slot through which the tip of 311 is passed during manufacture. It tapers to a neck at the end of the threaded portion and a knob is supplied such that the neck slides within the knob, but the knob and threaded portion limit the movement of the slot on the shaft. As the shaft 311 extends, the ramp of 314, now seated in slot 357 with its tip wrapping around the neck of the shaft, will cause the cowling to raise and pivot up. When the cowling becomes upright and the shaft is now completely extended (reference numeral 356), the shaft begins to turn and screws the threaded portion into the hub of the fan. After operation, the pump-motor 327 can be reversed to unscrew it. Then, upon retraction, the knob will pull the slot with it, collapsing the fan into the wing. 345 shows the ailerons in their relation to the flaps 353. 358 and 359 are mounting arrangements for the shaft.

[0180] Inside the wing, the gas turbine engine reposes as shown in FIG. 20. FIGS. 20-22 serve to also show the different views of the combustor and will be nearly identical to how it will appear on the TF of FIG. 2. It is again here called TF because it is universal to the present application in all embodiments. TF has a top 363 of its housing which encases the centrifugal compressor and turbine, whose inlet and outlet are, respectively, 364 and 365. 361 corresponds to 33 in FIG. 2 and is the passage from the last compressor stage output into the combustor C or 362. 360 is the guide structure for leading air from the combustion chamber C to strike the vanes of T1. This is shown in FIG. 21 and includes vanes 372 and 373. 371 is the space between the outer wall of 362 and the combustion chamber geometry 370, and assists in surrounding the chamber with air to be led into it FIG. 22 shows four guide structures 375 leading to four combustion areas 374. It is noted that the combustor inlet 361 would appear like a mirror image of FIG. 21 if portrayed.

[0181] At the top of FIG. 20 is an arrangement for placing all of the units within the wing in communication with each other. The inlet to the combustor communicates with this rail via path 369, as the turbine outlet does via 368. The combustor inlet 361 and outlet 360 communicate with the rail along path 366 and 367 and 366a and 367a, respectively. All four of these paths connect to the rail, which has a tube for each of the four airflows. 379 is a turreted, cylindrical valve with openings designed to transfer, at different degrees of rotation, the flow between any one passage and any other, and between any of them and, through the openings shown in the exposed portion of the rail, with the pressure accumulator. Each longitudinal zone of this valve will have a different set of borings, such that when the valve is turned a certain amount in one direction, the airflow seen in FIG. 23 becomes realized. Turning a little more would yield FIG. 24, and a little more would yield FIG. 25, and so on for further utilizations. The different schemes shown for driving different compressors with different turbines and different turbines or compressors with different pump-motors are by no means to be considered exhaustive. There are likely dozens of scenarios whereby the various compressors and turbines and pump-motors of the several units could be valved to enhance the efficiency. But to begin with, the maximum power output would be all units running full, with cowlings up and flaps down, for vertical take-off. The extra scenarios are envisioned for achieving different cruising speeds while minimizing fuel burn.

[0182] FIG. 26 show a third embodiment of the invention. 402 is again the TF from the first embodiment. The inlet 401 has no special features and the turbine outlet could go anywhere into the body 400 which is a pressure accumulator except where the cabin resides. 403 is a drive arrangement and transmission for coupling the output shaft of the TF directly to the drive wheels of the vehicle, which is a little tow truck. It can hardly be considered a truck going by the dimensions shown in FIG. 27. 409 indicates the cabin and 405 indicates the airflow from the pressure accumulator to a bank of pump motors 407 stored in the tongue of the truck. The driven wheels are oversized relative to the truck because they must support the weight of a towed object, as described later. 410 is the bulk of the pressure accumulator. This is a collapsible chamber that when extended takes the form shown in FIG. 26 and when collapsed takes the shape shown in FIG. 27. The tongue 413, 406 is adapted to have its wheels 411 attached 412 and removed via a slide-up arrangement 414 which lets the axles slip up and out when a pin is pulled out.

[0183] In operation the truck drives around in hybrid mode, answering to a dispatch service. It should get the gas mileage of a very small car operating with the pressure accumulator 410 very large such that the TF pumps it full and it can drive around for a substantial time before requiring recharge. However, when the truck arrives at the scene of a vehicle 418 to be towed, the chamber collapses to the configuration shown in FIG. 27, and the tow truck assumes a position directly in front of the vehicle 418. The operator removes the wheels and the tongue sinks (any number of mechanisms can be used to soften this and/or protect the tongue) to the road and the tow truck backs up, resulting in the tongue extending partway under the vehicle 418 and between its front wheels. The operator throws a strap 416 over the hood of the vehicle 418 and ratchets it down as per the arrow 417. The TF then commences combustion and charges the pressure accumulator 410 against the undercarriage of the vehicle 418. Once a pressure of 3 or 5 atmospheres has been reached (3 atmospheres is 2 atm over barometric, which will yield 28 psi in force, easily jacking even the largest vehicle and if not the pressure will reach many more atmospheres before the pump/motor is activated), the expanding chamber 410 causes a torque 415 about the back rim of the tongue and the configuration shown in FIG. 28 will be soon reached. The tow truck now operates as does the first embodiment during flight, with adjustments for the transmission and other requisite accoutrement. The TF will be very powerful compared to the tow truck's weight itself, but would be set to match the horsepower of a large truck, which is generally less than 500 HP, such that the turbine should not have to be very large. The pump/motors will continue to operate in this condition but slightly differently from the first embodiment.

APPENDIX I

[0184] Of the types of expanders foreseen as the pump/motor (PM1) are: [0185] a) a single piston-cylinder with one or more control valve(s); [0186] b) multiple piston-cylinders with a single, or multiple, control valve(s); [0187] c) a single centrifugal turbine of non-variable rotor and/or stator vanes; [0188] d) a single centrifugal turbine with variable rotor and/or stator vanes; [0189] e) multiple centrifugal turbines of non-variable rotor and/or stator; [0190] f) multiple centrifugal turbines of variable rotor and/or stator vanes; [0191] g) multiple axial turbines of variable or fixed rotor and/or stator vanes. [0192] h) of the foregoing, a+b; [0193] i) of the foregoing, a+c; [0194] j) of the foregoing, a+d; [0195] k) of the foregoing, a+e; [0196] l) of the foregoing, a+f; [0197] m) of the foregoing, a+g; [0198] n) of the foregoing, b+c; [0199] o) of the foregoing, b+d; [0200] p) of the foregoing, b+e; [0201] q) of the foregoing, b+f; [0202] r) of the foregoing, b+g; [0203] s) of the foregoing, c+d; [0204] t) of the foregoing, c+e; [0205] u) of the foregoing, c+f; [0206] v) of the foregoing, c+g; [0207] w) of the foregoing, d+e; [0208] x) of the foregoing, d+f; [0209] y) of the foregoing, d+g; [0210] z) of the foregoing, e+f; [0211] aa) of the foregoing, e+g; [0212] ab) of the foregoing, a+h; [0213] ac) of the foregoing, a+i, a+j, a+k, a+1, a+m, a+n, a+o, a+p, a+q, a+r, a+s, a+t, a+u, a+v, a+w, a+x, a+y, a+z, a+aa, or a+ab; [0214] ad) of the foregoing, b+i, b+j, b+k, b+1, b+m, b+n, b+o, b+p, b+q, b+r, b+s, b+t, b+u, b+v, b+w, b+x, b+y, b+z, b+aa, or b+ab; [0215] ae) of the foregoing, c+i, c+j, c+k, c+1, c+m, c+n, c+o, c+p, c+q, c+r, c+s, c+t, c+u, c+v, c+w, c+x, c+y, c+z, c+aa, or c+ab; [0216] af) of the foregoing, d+i, d+j, d+k, d+1, d+m, d+n, d+o, d+p, d+q, d+r, d+s, d+t, d+u, d+v, d+w, d+x, d+y, d+z, d+aa, or d+ab; [0217] ag) of the foregoing, e+i, e+j, e+k, e+1, e+m, e+n, e+o, e+p, e+q, e+r, e+s, e+t, e+u, e+v, e+w, e+x, e+y, e+z, e+aa, or e+ab; [0218] ah) of the foregoing, e+i, e+j, e+k, e+1, e+m, e+n, e+o, e+p, e+q, e+r, e+s, e+t, e+u, e+v, e+w, e+x, e+y, e+z, e+aa, or e+ab; [0219] ai) of the foregoing, f+i, f+j, f+k, f+1, f+m, f+n, f+o, f+p, f+q, f+r, f+s, f+t, f+u, f+v, f+w, f+x, f+y, f+z, f+aa, or f+ab; [0220] aj) of the foregoing, g+i, g+j, g+k, g+1, g+m, g+n, g+o, g+p, g+q, g+r, g+s, g+t, g+u, g+v, g+w, g+x, g+y, g+z, g+aa, or g+ab.