Aircraft

Abstract

To suppress the discharge amount of nitrogen oxide in an aircraft.SOLUTION: An aircraft 1 includes: a fuselage 2; a case 32 provided at the fuselage, and configured for defining an air chamber 31; a gas turbine engine 10 arranged in the air chamber; a first rotary electric machine 11 provided at the fuselage, and connected to an output shaft 16 of the gas turbine engine; a battery 14 provided at the fuselage, and connected to the first rotary electric machine; a second rotary electric machine 12 provided at the fuselage, and connected to the battery; and a propeller 13 provided at the rotary shaft of the second rotary electric machine. The case includes a first case intake port 35, and a case exhaust port 36. The gas turbine engine includes an intake port 25 and an exhaust port 26. The gas turbine engine is arranged in the air chamber in such a manner that the intake port is arranged on the first case intake port side and the exhaust port is arranged on the case exhaust port side. At the intake port, a separation membrane 50 is provided which transmits oxygen but inhibits transmission of nitrogen.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to an aircraft.

Background Art

[0002] Conventionally, efforts for mitigating climate change or reducing its impacts have been continued, and research and development related to aircraft have been conducted towards this realization. Patent Document 1 discloses an aircraft having a power source including a gas turbine engine and a generator, a battery, and a fan assembly driven by electric power from the power source or the battery. By electrifying the propulsion device, nitrogen oxides and carbon dioxide emitted from the aircraft can be reduced.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] However, since a gas turbine engine emits nitrogen oxides, further reduction of nitrogen oxides is desired.

[0005] In view of the above background, an object of the present invention is to suppress the emission amount of nitrogen oxides in an aircraft. And the present invention aims to contribute to mitigating climate change or reducing its impacts.

Means for Solving the Problems

[0006] To solve the above problems, an aspect of the present invention is an aircraft (1), comprising: a fuselage (2); a case (32) provided on the fuselage and defining an air chamber (31); a gas turbine engine (10) disposed in the air chamber; a first rotating electrical machine (11) provided on the fuselage and connected to the output shaft (16) of the gas turbine engine; a battery (14) provided on the fuselage and connected to the first rotating electrical machine; a second rotating electrical machine (12) provided on the fuselage and connected to the battery; and a propeller 13 provided on the rotating shaft of the second rotating electrical machine. The case has a first case air inlet (35) and a case air outlet (36). The gas turbine engine has an air inlet (25) and an exhaust outlet (26). The gas turbine engine is disposed in the air chamber such that the air inlet is disposed on the side of the first case air inlet and the exhaust outlet is disposed on the side of the case air outlet. A separation membrane (50) that allows oxygen to permeate while blocking the permeation of nitrogen is provided at the air inlet.

[0007] According to this aspect, the separation membrane supplies oxygen-enriched air having a higher oxygen concentration and a lower nitrogen concentration than air to the gas turbine engine. Therefore, the amount of nitrogen oxides generated in the gas turbine engine can be reduced. That is, in the aircraft, the emission amount of nitrogen oxides can be suppressed. This effect contributes to the mitigation or reduction of the impact of climate change. Further, the air that has not passed through the separation membrane flows through the case along the outer surface of the gas turbine engine to the case air outlet, thereby cooling the gas turbine engine.

[0008] In the above aspect, the case and the output shaft of the gas turbine engine may extend in the vertical direction, the first case air inlet may be disposed at the upper end of the case, and the case air outlet may be disposed at the lower end of the case and open downward.

[0009] According to this aspect, since the exhaust outlet of the gas turbine engine and the case air outlet face downward and the exhaust is discharged downward, the kinetic energy of the exhaust can be converted into the buoyancy of the fuselage.

[0010] In the above aspect, the first case air intake is arranged to open forward on the front surface of the upper end of the case, and the air intake of the gas turbine engine may open upward at the upper end of the air chamber.

[0011] According to this aspect, since the air intake of the gas turbine engine and the separation membrane do not face the first case air intake, it is possible to prevent the air flowing into the air chamber from the first case air intake from directly hitting the separation membrane from the front. As a result, it is possible to prevent dust and raindrops in the air from adhering to the separation membrane.

[0012] In the above aspect, the upper end of the case may reach the upper surface (3A) of the airframe, and the lower end of the case may reach the lower surface (3B) of the airframe.

[0013] According to this aspect, the case air intake and the case exhaust port can be brought closer to the outer surface of the airframe, and the intake and exhaust of air to and from the air chamber can be made smooth.

[0014] In the above aspect, the upper surface of the airframe constitutes the upper end surface of the case, and a wind guiding groove (39) that is recessed downward and extends in the front-rear direction is formed on the upper surface of the airframe. The wind guiding groove has a depth that gradually increases toward the rear and may be connected to the first case air intake at the rear end.

[0015] According to this aspect, it is possible to reduce the influence of the upper end of the case on the air resistance of the airframe.

[0016] In the above aspect, a second case air intake (41) that opens upward and a wind guiding device (42) that opens and closes the second case air intake and guides air to the second case air intake may be provided at the upper end of the case.

[0017] According to this aspect, the second case air intake can supply air to the front of the air intake of the gas turbine engine and the separation membrane.

[0018] In the above aspect, the air guiding device may include a plurality of guide plates (42A) rotatably provided at the upper end of the case, and an electric actuator (42B) for rotating the plurality of guide plates.

[0019] According to this aspect, the amount of air supplied to the intake port of the gas turbine engine and the front of the separation membrane can be adjusted by the guide plates.

[0020] In the above aspect, the exhaust port of the gas turbine engine may open downward so as to face the case exhaust port.

[0021] According to this aspect, the exhaust of the gas turbine engine can flow smoothly to the case exhaust port, and the kinetic energy of the exhaust can be efficiently converted into the buoyancy of the aircraft.

[0022] In the above aspect, the gas turbine engine, the first rotating electric machine, the battery, the second rotating electric machine, and a control device (60) connected to the air guiding device are included, and the control device may be configured to control the gas turbine engine and the first rotating electric machine according to the SOC of the battery.

[0023] According to this aspect, the power generation by the gas turbine engine and the generator can be controlled according to the SOC of the battery.

[0024] In the above aspect, the control device may be configured to drive the gas turbine engine and open the air guiding device when the aircraft ascends.

[0025] According to this aspect, when the aircraft with a large power consumption ascends, the gas turbine engine can be driven to suppress the decrease in the SOC of the battery.

[0026] In the above aspect, the control device may be configured to reduce the opening degree of the air guiding device when the aircraft moves forward.

[0027] According to this aspect, when the forward movement of the aircraft is predicted, the second case air intake is closed, so the air resistance caused by the air guiding device is reduced.

[0028] In the above aspect, the control device may be configured to reduce the opening degree of the air guiding device as the forward speed of the aircraft increases when the aircraft is moving forward.

[0029] According to this aspect, when the aircraft reduces its forward speed to prepare for landing, air can be supplied to the gas turbine engine through the air guiding device.

Advantages of the Invention

[0030] According to the above configuration, in an aircraft, the emission amount of nitrogen oxides can be suppressed. Also, it can contribute to the mitigation or reduction of the impact of climate change.

Brief Description of the Drawings

[0031]

Figure 1

Figure 2

Figure 3

Figure 4

Modes for Carrying Out the Invention

[0032] Hereinafter, with reference to the drawings, embodiments of the aircraft according to the present invention will be described. The aircraft may be a so-called eVTOL (electric vertical take-off and landing aircraft, Electric Vertical Take Off and Landing aircraft) or an electric multicopter.

[0033] As shown in FIG. 1, the fuselage 2 of the aircraft 1 has a fuselage main body 3 extending longitudinally, a front wing 4 and a rear wing 5 extending laterally from the fuselage main body 3, and left and right arms 7 extending longitudinally and coupled to the front wing 4 and the rear wing 5. A cabin 8 for passengers to board is provided in the fuselage main body 3. The front wing 4 and the rear wing 5 may be formed in a shape that generates lift with respect to forward movement.

[0034] As shown in FIG. 2, the aircraft 1 has a gas turbine engine 10, a first rotating electric machine 11, a second rotating electric machine 12, a propeller 13, and a battery 14. The first rotating electric machine 11 is connected to the output shaft 16 of the gas turbine engine 10. The first rotating electric machine 11 is driven by the gas turbine engine 10 to generate electricity. The battery 14 is connected to the first rotating electric machine 11 and is charged by receiving power supply from the first rotating electric machine 11.

[0035] As shown in FIG. 1, the propeller 13 is coupled to the rotating shaft of the second rotating electric machine 12. The combination of the propeller 13 and the second rotating electric machine 12 constitutes a vertical propulsion device 18 or a horizontal propulsion device 19. In this embodiment, the aircraft 1 has a plurality of vertical propulsion devices 18 and a plurality of horizontal propulsion devices 19.

[0036] The plurality of vertical propulsion devices 18 are provided on the left and right arms 7. Each vertical propulsion device 18 generates thrust in the vertical direction. Each vertical propulsion device 18 is arranged on the arm 7 at intervals in the front-rear direction so as not to interfere with each other. The second rotating electric machine 12 of each vertical propulsion device 18 is coupled to the corresponding arm 7 such that the rotating shaft extends in the vertical direction.

[0037] The plurality of horizontal propulsion devices 19 are provided at the rear end of the fuselage main body 3. Each horizontal propulsion device 19 generates thrust in the horizontal direction. Each horizontal propulsion device 19 is arranged side by side in the left-right direction so as not to interfere with each other. The second rotating electric machine 12 of each horizontal propulsion device 19 has a rotating shaft extending in the horizontal direction.

[0038] As shown in FIG. 3, the gas turbine engine 10 has a compressor 21, a combustor 22, and a turbine 23. The compressor 21 and the turbine 23 are arranged along the axis A of the gas turbine engine 10. The compressor 21 is an axial-flow compressor. The compressor 21 has a cylindrical compressor housing 21A and a compressor rotor 21B rotatably supported within the compressor housing 21A. An air inlet 25 is formed at one end of the compressor housing 21A in the axial direction. The air inlet 25 communicates with the internal space of the compressor housing 21A. A plurality of compressor rotor blades 21C are provided on the outer peripheral surface of the compressor rotor 21B, and a plurality of compressor stator blades 21D are provided on the inner peripheral surface of the compressor housing 21A. The plurality of compressor rotor blades 21C and the plurality of compressor stator blades 21D are alternately arranged in the axial direction. A diffuser 21E is provided at one end of the compressor housing 21A in the axial direction. When the compressor rotor 21B rotates, air is inhaled from the air inlet 25. The inhaled air is compressed by the compressor rotor blades 21C and the compressor stator blades 21D and sent to the combustor 22 via the diffuser 21E.

[0039] The combustor 22 mixes fuel with the compressed air supplied from the compressor 21 and burns it to generate high-temperature and high-pressure combustion gas. The fuel may be a known hydrocarbon fuel such as kerosene or light oil.

[0040] The turbine 23 is an axial-flow turbine. The turbine 23 has a cylindrical turbine housing 23A and a turbine rotor 23B rotatably supported within the turbine housing 23A. A turbine inlet 23C is formed at the end of the turbine housing 23A on the compressor 21 side in the axial direction. The turbine inlet 23C is connected to the combustor 22. An exhaust port 26 is formed at the end of the turbine housing 23A on the side opposite to the compressor 21 in the axial direction. A plurality of turbine moving blades 23D are provided on the outer peripheral surface of the turbine rotor 23B, and a plurality of turbine stationary blades 23E are provided on the inner peripheral surface of the turbine housing 23A. The plurality of turbine moving blades 23D and the plurality of turbine stationary blades 23E are alternately arranged in the axial direction. The compressor rotor 21B and the turbine rotor 23B are coupled to each other by a connecting shaft 29. An output shaft 16 is connected to the turbine rotor 23B. The combustion gas supplied from the combustor 22 collides with the turbine moving blades 23D to rotate the turbine rotor 23B. The fuel gas that has passed through the turbine moving blades 23D and the turbine stationary blades 23E is discharged to the outside from the exhaust port 26.

[0041] The intake port 25 is disposed at one end of the gas turbine engine 10 in the axial direction. The exhaust port 26 is disposed at the other end of the gas turbine engine 10 in the axial direction.

[0042] As shown in FIGS. 1 and 3, the airframe 2 is provided with a case 32 that defines an air chamber 31. In the present embodiment, the case 32 is provided on the airframe main body 3. The case 32 may be provided behind the cabin 8 in the airframe main body 3. Further, the case 32 may be provided in front of each horizontal propulsion device 19 in the airframe main body 3. The gas turbine engine 10 is disposed within the air chamber 31. Each of the gas turbine engine 10 and the case 32 may be supported by the frame of the airframe main body 3.

[0043] As shown in FIG. 3, the case 32 extends in the vertical direction. The case 32 has a first case air inlet 35 and a case air outlet 36. The first case air inlet 35 is disposed at the upper end of the case 32. The first case air inlet 35 is disposed so as to open forward on the front surface of the upper end of the case 32. The case air outlet 36 is disposed so as to open downward at the lower end of the case 32.

[0044] It is preferable that the upper end of the case 32 reaches the upper surface 3A of the machine body 3. Also, it is preferable that the lower end of the case 32 reaches the lower surface 3B of the machine body 3. The upper surface 3A of the machine body 3 may constitute the upper end surface of the case 32. A wind guide groove 39 that is recessed downward and extends in the front-rear direction is formed on the upper surface 3A of the machine body 3. The wind guide groove 39 has a depth that gradually increases toward the rear and is connected to the first case air inlet 35 at the rear end.

[0045] At the upper end of the case 32, a second case air inlet 41 that opens upward and a wind guide device 42 that opens and closes the second case air inlet 41 and guides air to the second case air inlet 41 are provided. The wind guide device 42 has a plurality of guide plates 42A rotatably provided at the upper end of the case 32 and an electric actuator 42B that rotates the plurality of guide plates 42A. Each guide plate 42A extends in the left-right direction and may rotate about a rotation axis extending in the left-right direction. Each rotation axis may be provided at the rear end of each guide plate 42A or at the center of each guide plate 42A in the front-rear direction. When each guide plate 42A rotates outward of the machine body 2, the wind guide device 42 opens.

[0046] An exhaust device 45 is provided at the exhaust port 26 for opening and closing the exhaust port 26 and changing the exhaust discharge direction. The exhaust device 45 includes a plurality of guide plates 45A rotatably provided at the lower end of the case 32, and an electric actuator 45B for rotating the plurality of guide plates 45A. Each guide plate 45A may extend in the left-right direction and rotate about a rotation axis extending in the left-right direction. Each rotation axis may be provided at the front end of each guide plate 45A or at the center of each guide plate 45A in the front-rear direction.

[0047] The gas turbine engine 10 is disposed in the air chamber 31. The gas turbine engine 10 is disposed in the air chamber 31 such that the axis A extends in the vertical direction and the intake port 25 is located on the upper side. That is, the gas turbine engine 10 is disposed in the air chamber 31 such that the intake port 25 is disposed on the side of the first case intake port 35 and the exhaust port 26 is disposed on the side of the case exhaust port 36. The axis A and the output shaft 16 of the gas turbine engine 10 extend in the vertical direction. Thereby, the axis A and the output shaft 16 of the gas turbine engine 10 are disposed perpendicular to the traveling direction of the aircraft 1.

[0048] The intake port 25 of the gas turbine engine 10 opens upward at the upper end of the air chamber 31. The intake port 25 faces the upper end of the case 32 with a gap therebetween. Further, the intake port 25 faces the second case intake port 41 with a gap therebetween. Since the intake port 25 opens upward and the first case intake port 35 opens forward, the opening direction of the intake port 25 is perpendicular to the opening direction of the first case intake port 35. The exhaust port 26 of the gas turbine engine 10 opens downward so as to face the case exhaust port 36.

[0049] The intake port 25 is provided with a separation membrane 50 that allows oxygen to permeate while blocking the permeation of nitrogen. The separation membrane 50 is formed of a material that allows oxygen to permeate while inhibiting the permeation of nitrogen. The separation membrane 50 may be, for example, graphene having nano-windows. The nano-windows are formed by lacking some carbon atoms in the graphene. The nano-windows may be designed such that oxygen permeates more easily than nitrogen. One or more atoms constituting the rim of the nano-windows may be replaced with heteroatoms. The heteroatoms may be, for example, oxygen, nitrogen, sulfur, phosphorus, chlorine, iodine, bromine, or boron atoms. The van der Waals diameter of the nano-windows may be 2.97 Å. The separation membrane 50 has an oxygen permeation rate constant of 47 μs -1 and may have a selectivity such that the permeation of oxygen is more than 50 times greater than the permeation of nitrogen. For details of the separation membrane 50, see, for example, WO2019 / 013059A1.

[0050] The separation membrane 50 is formed in a planar shape and is arranged to cover the intake port 25. The separation membrane 50 may be supported by a breathable sheet-like support member 51. The separation membrane 50 may be sandwiched between a pair of support members 51. The separation membrane 50 and the support member 51 may be joined to each other at the edges. The separation membrane 50 and the support member 51 may have a pleated structure to increase the surface area. The edges of the separation membrane 50 and the support member 51 may be joined to a frame 52. The frame 52 may be provided with a plurality of beams 53 that support the separation membrane 50 and the support member 51 from the back side. The separation membrane 50, the support member 51, the frame 52, and the plurality of beams 53 may be unitized as a separation membrane assembly 55.

[0051] The separation membrane assembly 55 may be mounted inside the intake port 25. A receiving portion 57 into which the separation membrane assembly 55 is fitted is formed on the inner peripheral surface of the intake port 25. The receiving portion 57 has a shoulder surface facing the opening end side of the intake port 25 and supports the edge of the separation membrane assembly 55 at the shoulder surface.

[0052] The case 32 is provided with a heat exchanger 58 that performs heat exchange between the air flowing inside the case 32 and the air inside the cabin 8. The heat exchanger 58 may be provided inside the case 32 or outside the case 32. The heat exchange may be provided on the downstream side of the case 32, that is, on the case exhaust port 36 side.

[0053] As shown in FIG. 4, the aircraft 1 has a control device 60. The control device 60 is an electronic control device and is an arithmetic device having a microprocessor (MPU), a non-volatile memory, a volatile memory, and an interface. The control device 60 realizes various applications by the microprocessor executing a program stored in the non-volatile memory. The control device 60 may be formed by a single unit or may be formed by a plurality of units that cooperate with each other.

[0054] The control device 60 is connected to the gas turbine engine 10, the first rotating electrical machine 11, the battery 14, the plurality of second rotating electrical machines 12, the air guiding device 42, and the exhaust device 45. Further, the control device 60 is connected to various sensors provided on the aircraft 1. The sensors may include, for example, an acceleration sensor 62A, an altitude sensor 62B, etc. The altitude sensor 62B measures the altitude of the aircraft 1. The altitude sensor 62B may measure the altitude of the aircraft 1 from the ground surface or the water surface, for example, by irradiating electromagnetic waves downward and measuring the reflected waves. The acceleration sensor 62A may be a gyro sensor and may detect longitudinal acceleration, vertical acceleration, and lateral acceleration. The control device 60 may calculate the longitudinal speed, vertical speed, and lateral speed based on the longitudinal acceleration, vertical acceleration, and lateral acceleration detected by the acceleration sensor 62A.

[0055] Further, the control device 60 may be connected to an operating device 64 operated by a crew member boarding the cabin 8. The operating device 64 may output a signal corresponding to, for example, the ascent, descent, forward movement, backward movement, left turn, and right turn of the aircraft 1 to the control device 60 according to the operation of the crew member.

[0056] The control device 60 determines the SOC of the battery 14. The control device 60 may detect the SOC based on, for example, the potential of the battery 14.

[0057] The control device 60 is configured to control each second rotating electric machine 12 to adjust the altitude, attitude, and speed of the aircraft 1 based on signals from the operating device 64 and each sensor 62A, 62B. For example, the control device 60 may set a longitudinal speed target value and a vertical speed target value based on a signal from the operating device 64, and control a plurality of second rotating electric machines 12 so that the current longitudinal speed and vertical speed become the longitudinal speed target value and the vertical speed target value. The longitudinal speed has a positive value on the forward side and a negative value on the reverse side. The vertical speed has a positive value on the ascending side and a negative value on the descending side.

[0058] Also, the control device 60 may be configured to control the gas turbine engine 10 and the first rotating electric machine 11 according to the SOC of the battery 14. Further, the control device 60 may be configured to control the gas turbine engine 10, the first rotating electric machine 11, the air guiding device 42, and the exhaust device 45 based on the state of the aircraft 1. The state of the aircraft 1 may include at least one of the longitudinal speed, vertical speed, and altitude of the aircraft 1.

[0059] The control device 60 may be configured to drive the gas turbine engine 10 and control the first rotating electric machine 11 when the SOC is equal to or lower than a predetermined SOC threshold value. Thereby, the first rotating electric machine 11 generates electricity by receiving the driving force of the gas turbine engine 10, and charges the battery 14. Thereby, the SOC of the battery 14 increases.

[0060] The control device 60 may be configured to drive the gas turbine engine 10 and open the air guiding device 42 when the airframe 2 ascends. The control device 60 may determine the ascent of the airframe 2 based on the speed or acceleration in the ascending direction. Further, the control device 60 may determine the ascent of the airframe 2 based on the vertical speed target value. When the airframe 2 ascends, the power consumption of each second rotating electric machine 12 increases, so the first rotating electric machine 11 charges to suppress the decrease in the SOC of the battery 14. Also, since the exhaust gas of the gas turbine engine 10 is discharged downward from the case exhaust port 36, the kinetic energy of the exhaust gas can be utilized for the ascent of the airframe 2. When the airframe 2 ascends, the second case intake port 41 is opened by the air guiding device 42, so the air supplied to the intake port 25 of the gas turbine engine 10 increases.

[0061] The control device 60 may be configured to reduce the opening degree of the air guiding device 42 when the airframe 2 moves forward. The control device 60 may determine the forward movement of the airframe 2 based on the speed or acceleration in the forward direction. Further, the control device 60 may determine the forward movement of the airframe 2 based on the forward and backward speed target value. When the airframe 2 moves forward, the opening degree of the air guiding device 42 becomes smaller, so the air resistance caused by the air guiding device 42 becomes smaller. Thereby, the energy efficiency of the aircraft 1 is improved. In a state where the opening degree of the air guiding device 42 is small, the gas turbine engine 10 may be driven or may be stopped. The gas turbine engine 10 is supplied with air flowing in from the first case intake port 35. The control device 60 may be configured to fully close the air guiding device 42 when the airframe 2 moves forward.

[0062] Further, the control device 60 may be configured to reduce the opening degree of the air guiding device 42 as the forward speed of the airframe 2 increases when the airframe 2 moves forward. Thereby, when the airframe 2 reduces its forward speed to prepare for landing, the amount of air supplied to the gas turbine engine 10 by opening the air guiding device 42 can be increased.

[0063] The operation and effects of the aircraft 1 configured as described above will be described. As shown in FIG. 3, the air outside the fuselage 2 flows into the air chamber 31 through the first case intake port 35 and the second case intake port 41. The gas turbine engine 10 inhales the air in the air chamber 31 through the intake port 25 provided with the separation membrane 50. The separation membrane 50 provided at the intake port 25 of the gas turbine engine 10 has selectivity to permeate more oxygen than nitrogen. Therefore, the air sucked into the intake port 25 through the separation membrane 50 becomes an oxygen-enriched gas with a higher oxygen concentration and a lower nitrogen concentration than air. The oxygen-enriched gas that has passed through the separation membrane 50 is more preferably lower in nitrogen concentration, and preferably contains almost no nitrogen.

[0064] When the oxygen-enriched gas is used as the combustion support gas, the amount of nitrogen oxides generated during combustion can be reduced compared to the case where air is used as the combustion support gas. Therefore, the amount of nitrogen oxides generated in the gas turbine engine 10 can be reduced. That is, in the aircraft 1, the emission amount of nitrogen oxides can be suppressed. Further, since the amount of nitrogen oxides generated is small, the combustion temperature can be increased, and the fuel efficiency can be improved. When the oxygen-enriched gas is used as the combustion support gas, the volume of the combustion support gas can be reduced compared to the case where air is used as the combustion support gas, so that the gas turbine engine 10 can be miniaturized and lightened. Thereby, the fuel efficiency can be improved. By improving the fuel efficiency, the flight range of the aircraft 1 can be extended.

[0065] The air that has not passed through the separation membrane 50 becomes a nitrogen-enriched gas with a lower oxygen concentration and a higher nitrogen concentration than air. The nitrogen-enriched gas flows from the intake port 25 of the gas turbine engine 10 through the gap between the outer surface of the gas turbine engine 10 and the inner surface of the case 32 to the case exhaust port 36. At this time, the nitrogen-enriched gas cools the gas turbine engine 10. A part of the nitrogen-enriched gas heated on the surface of the gas turbine engine 10 passes through the heat exchanger 58 and heats the air circulating in the cabin 8 and the heat exchanger. That is, the thermal energy radiated from the outer surface of the gas turbine engine 10 is used for heating the cabin 8.

[0066] The opening direction of the intake port 35 of the first case and the opening direction of the intake port 25 of the gas turbine engine 10 are perpendicular to each other and do not face each other. Therefore, it is suppressed that the air flowing into the air chamber 31 from the intake port 35 of the first case directly hits the separation membrane 50 from the front. Thereby, it is possible to suppress dust and raindrops in the air from adhering to the separation membrane 50. Further, the wind pressure applied to the separation membrane 50 can be reduced.

[0067] The exhaust port 26 of the gas turbine engine 10 and the case exhaust port 36 face downward, and since the exhaust is discharged downward, the kinetic energy of the exhaust can be converted into the buoyancy of the airframe 2. Further, the exhaust port 26 of the gas turbine engine 10 and the case exhaust port 36 face each other, and since the exhaust smoothly flows from the exhaust port 26 of the gas turbine engine 10 to the case exhaust port 36, the pressure near the case exhaust port 36 of the air chamber 31 decreases. Thereby, the flow of the gas flowing from the first case intake port 35 side to the case exhaust port 36 side is promoted. As a result, the cooling of the gas turbine engine 10 is promoted.

[0068] Since the second case intake port 41 and the air guiding device 42 for opening and closing the second case intake port 41 are provided at the upper end of the case 32, by opening the air guiding device 42, air can be supplied to the front of the intake port 25 of the gas turbine engine 10 and the separation membrane 50. Thereby, when it is desired to increase the output of the gas turbine engine 10, sufficient air can be supplied to the gas turbine engine 10. Further, by adjusting the opening degree and angle of the guide plate 42A of the air guiding device 42, the amount of air supplied to the front of the intake port 25 of the gas turbine engine 10 and the separation membrane 50 can be adjusted.

[0069] With the above, the description of the specific embodiment is completed, but the present invention can be widely modified and implemented without being limited to the above embodiment. For example, the number of the vertical propulsion devices 18 and the horizontal propulsion devices 19 can be arbitrarily changed, and the horizontal propulsion device 19 may be omitted. Each propeller 13 may be replaced with a rotor having no blade twist angle.

[0070] The upper end of the case 32 may protrude upward from the upper surface 3A of the aircraft body 3. In this case, the first case air inlet 35 may be disposed above the upper surface 3A of the aircraft body 3.

[0071] The control device 60 may control the exhaust device 45 so that the exhaust discharge direction faces backward when the aircraft 1 moves forward. Further, the control device 60 may fully close the exhaust device 45 when the gas turbine engine 10 stops.

[0072] When the air inlet 25 of the gas turbine engine 10 is divided into a plurality, a separation film 50 may be provided for each of the plurality of divided air inlets 25.

[0073] The control device 60 may perform regenerative control on the second rotating electric machine 12 of the vertical propulsion device 18 to charge the battery 14 when the aircraft 1 moves forward or backward. Further, the control device 60 may rotationally drive the first rotating electric machine 11 when starting the gas turbine engine 10, and rotate the output shaft 16 of the gas turbine engine 10 by the driving force of the first rotating electric machine 11.

Explanation of Reference Numerals

[0074] 1: Aircraft 2: Airframe 3: Aircraft body 3A: Upper surface 3B: Lower surface 10: Gas turbine engine 11: First rotating electric machine 12: Second rotating electric machine 13: Propeller 14: Battery 16: Output shaft 18: Vertical propulsion device 19: Horizontal propulsion device 25: Air inlet 26: Exhaust port 29: Connecting shaft 31: Air chamber 32: Case 35: First case air inlet 36: Case exhaust port 39: Air guide groove 41: Second case intake port 42: Air guiding device 42A: Guide plate 42B: Electric actuator 45: Exhaust device 50: Separation membrane 60: Control device

Claims

1. An aircraft comprising: a fuselage; a case provided on the fuselage and defining an air chamber; a gas turbine engine disposed in the air chamber; a first rotating electric machine provided on the fuselage and connected to the output shaft of the gas turbine engine; a battery provided on the fuselage and connected to the first rotating electric machine; a second rotating electric machine provided on the fuselage and connected to the battery; a propeller provided on the rotating shaft of the second rotating electric machine, wherein the case has a first case air inlet and a case exhaust port; the gas turbine engine has an air inlet and an exhaust port; the gas turbine engine is disposed in the air chamber such that the air inlet is disposed on the side of the first case air inlet and the exhaust port is disposed on the side of the case exhaust port; and a separation membrane that allows oxygen to permeate while blocking the permeation of nitrogen is provided at the air inlet.

2. The output shafts of the case and the gas turbine engine extend in the vertical direction, the first case air inlet is disposed at the upper end of the case, and the case exhaust port is disposed at the lower end of the case so as to open downward. The aircraft according to claim 1.

3. The first case air inlet is disposed at the front surface of the upper end of the case so as to open forward, and the air inlet of the gas turbine engine opens upward at the upper end of the air chamber. The aircraft according to claim 2.

4. The upper end of the case reaches the upper surface of the fuselage, and the lower end of the case reaches the lower surface of the fuselage. The aircraft according to claim 3.

5. The upper surface of the fuselage constitutes the upper end surface of the case, a wind guiding groove that is recessed downward is formed on the upper surface of the fuselage, and the wind guiding groove has a depth that gradually increases rearward and is connected to the first case air inlet at the rear end. The aircraft according to claim 4.

6. A second case air inlet that opens upward, and a wind guiding device that opens and closes the second case air inlet and guides air to the second case air inlet are provided at the upper end of the case. The aircraft according to claim 5.

7. The wind guiding device includes a plurality of guide plates rotatably provided at the upper end of the case, and an electric actuator that rotates the plurality of guide plates. The aircraft according to claim 6.

8. The aircraft according to claim 2, wherein the exhaust port of the gas turbine engine opens downward so as to face the case exhaust port.

9. The aircraft has the gas turbine engine, the first rotating electrical machine, the battery, the second rotating electrical machine, and a control device connected to the air guiding device, The control device is configured to control the gas turbine engine and the first rotating electrical machine according to the state of charge (SOC) of the battery. The aircraft according to claim 7.

10. The control device is configured to drive the gas turbine engine and open the air guiding device when the aircraft ascends. The aircraft according to claim 9.

11. The control device is configured to reduce the opening degree of the air guiding device when the aircraft moves forward. The aircraft according to claim 9.

12. The control device is configured to reduce the opening degree of the air guiding device more as the forward speed of the aircraft is higher when the aircraft moves forward. The aircraft according to claim 9.

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