WO2023040183A1 - Moteur d'aéronef à énergie pneumatique et procédé d'entraînement d'aéronef - Google Patents

Moteur d'aéronef à énergie pneumatique et procédé d'entraînement d'aéronef Download PDF

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Publication number
WO2023040183A1
WO2023040183A1 PCT/CN2022/076888 CN2022076888W WO2023040183A1 WO 2023040183 A1 WO2023040183 A1 WO 2023040183A1 CN 2022076888 W CN2022076888 W CN 2022076888W WO 2023040183 A1 WO2023040183 A1 WO 2023040183A1
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Prior art keywords
temperature
energy
heat exchanger
aircraft
nacelle
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PCT/CN2022/076888
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English (en)
Chinese (zh)
Inventor
吴加林
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成都佳灵绿色能源有限责任公司
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Priority claimed from CN202111112192.1A external-priority patent/CN114248930A/zh
Application filed by 成都佳灵绿色能源有限责任公司 filed Critical 成都佳灵绿色能源有限责任公司
Publication of WO2023040183A1 publication Critical patent/WO2023040183A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants

Definitions

  • the invention relates to the technical field of engines, in particular to an air-powered aircraft engine and a method for driving the aircraft.
  • Airplanes are one of the symbols of modern civilization, but their fuel consumption accounts for more than one-third of their cost, and their flight costs are also one of the reasons that limit the increase in aircraft flight speed, and the carbon emissions and air pollution produced by aircraft burning fuel are also currently One of the more thorny problems, based on the above reasons, the behavior of human beings to expand their living space in the air is restricted. The existing aero-engines are also developing slowly due to high process requirements and scarcity of production materials.
  • thermodynamic energy is energy quantum, which is referred to as quantum for short.
  • Any object with a thermodynamic temperature above 0k has thermodynamic energy, and its essence is the energy generated by quantum motion.
  • the thermodynamic energy of any unit of matter and its thermodynamic temperature It is proportional to the specific heat and is also equal to the energy value in Planck's energy formula;
  • E is the energy
  • T is the thermodynamic temperature
  • C is the specific heat of the substance
  • N is the number of quanta
  • H is Planck's constant
  • V is the frequency of the quantum.
  • an air energy aircraft engine including a main cabin system and a nacelle system, and the nacelle system is configured in the nacelle of the aircraft, It is used to collect air energy and send it into the main cabin system, and at the same time, the external air is inhaled from the front of the nacelle to be pressurized and then ejected from the rear of the nacelle to generate thrust for the aircraft;
  • the main cabin system is arranged in the main cabin of the aircraft, It is used to convert low-temperature energy into high-temperature energy, and send high-temperature energy into the nacelle system, and the high-temperature energy sent into the nacelle is converted into mechanical energy as the driving force of the nacelle system.
  • the main cabin system includes a temperature changing device for converting low-temperature steam into high-temperature steam
  • the nacelle system includes a first steam turbine, a turbofan and a first heat exchanger, and the first The steam turbine is used to convert the high-temperature steam generated by the temperature changing device into mechanical energy, and then drive the turbofan, and at the same time deliver the generated exhaust air to the temperature changing device, and the turbofan is used to suck the external air into the nacelle and enter the outside of the nacelle
  • the air passes through the first heat exchanger to provide heat energy to the system working fluid in the first heat exchanger, and the system working fluid that absorbs heat energy is transformed into low-temperature steam and flows to the temperature changing device.
  • the temperature changing device includes a heat exchanger mechanism and a blower
  • the heat exchange mechanism has a low-pressure circuit and a high-pressure circuit
  • the inlet end of the blower communicates with the low-pressure circuit of the heat exchange mechanism
  • the outlet of the blower The end communicates with the high pressure circuit of the heat exchange mechanism.
  • the heat exchange mechanism includes a second heat exchanger, a heat recovery heat exchanger, and a third heat exchanger, and the heat recovery heat exchanger, the third heat exchanger, and a blower are connected in series in sequence, and the second heat exchanger The heat exchanger is connected in parallel with the third heat exchanger.
  • the temperature changing device further includes a temperature regulating valve, which is arranged in the high-pressure circuit of the temperature changing device, and is used to control the flow of high-temperature and high-pressure steam output by the blower between the second heat exchanger and the third heat exchanger. flow distribution, thereby controlling the temperature range of the high-temperature steam output by the second heat exchanger.
  • a temperature regulating valve which is arranged in the high-pressure circuit of the temperature changing device, and is used to control the flow of high-temperature and high-pressure steam output by the blower between the second heat exchanger and the third heat exchanger. flow distribution, thereby controlling the temperature range of the high-temperature steam output by the second heat exchanger.
  • the heat exchange mechanism further includes a fourth heat exchanger, and the fourth heat exchanger is used to increase the temperature difference between the high pressure circuit and the low pressure circuit at the high temperature end of the third heat exchanger.
  • blower and/or the third heat exchanger and/or the fourth heat exchanger and/or the second heat exchanger are provided with an insulation layer.
  • the main cabin system further includes a liquid storage tank, the liquid storage tank stores system working fluid, the liquid storage tank has a gas end and a liquid end, and the gas end of the liquid storage tank provides the temperature changing device Low-temperature steam, the liquid end of the liquid storage tank sucks the low-temperature liquid in the temperature changing device;
  • the system working fluid includes a refrigerant, and the refrigerant is one or more of nitrogen, R23 and air.
  • the main cabin system further includes a second steam turbine, an integrated motor generator and a storage battery; wherein, the second steam turbine and the first steam turbine are connected in parallel at the low-pressure inlet end of the temperature changing device and the high-pressure outlet end of the temperature changing device;
  • the mechanical energy end of the second steam turbine is mechanically connected to the temperature changing device, and is used to drive the blower in the temperature changing device through mechanical energy
  • the electric energy end of the second steam turbine is electrically connected to the battery through an integrated motor generator
  • the second steam turbine operates
  • the integrated motor-generator is driven at the same time as a generator to supplement electric energy for the battery;
  • the battery-driven integrated motor-generator is used as a motor to generate mechanical energy to drive the blower in the temperature changing device when starting.
  • the main cabin system further includes a second frequency converter, and the integrated motor generator is electrically connected to the storage battery through the second frequency converter.
  • the main cabin system further includes a regulating valve, which is used to regulate the flow rate of the gas working medium transmitted by the temperature changing device to the second steam turbine, thereby adjusting the rotation speed of the second steam turbine and the blower, thereby regulating the aircraft's flight speed.
  • a regulating valve which is used to regulate the flow rate of the gas working medium transmitted by the temperature changing device to the second steam turbine, thereby adjusting the rotation speed of the second steam turbine and the blower, thereby regulating the aircraft's flight speed.
  • the main cabin system further includes a liquid booster pump, one end of the liquid booster pump communicates with the liquid end of the liquid storage tank, and the other end communicates with the low-temperature inlet end of the first heat exchanger, and the liquid is pressurized
  • the pump is connected to the battery.
  • the main cabin system further includes a first frequency converter, and the power end of the liquid booster pump is electrically connected to the storage battery through the first frequency converter.
  • the main shaft of the first steam turbine is a magnetic suspension bearing.
  • the nacelle system further includes a vectoring nozzle configured at the rear end of the nacelle of the aircraft.
  • a reverse thrust device is provided at the outlet of the vectoring nozzle.
  • the turbofan is close to an end of the nacelle of the aircraft away from the thrust reverser.
  • a method for driving an aircraft by using the above-mentioned air energy aircraft engine comprising:
  • Air energy is collected through the nacelle system and sent to the main cabin system, while external air is inhaled from the front of the nacelle of the aircraft to be pressurized and then ejected from the rear of the nacelle, thereby generating thrust for the aircraft;
  • the low-temperature energy is converted into high-temperature energy through the main cabin system, and the high-temperature energy is sent into the nacelle system, and the high-temperature energy sent into the nacelle is converted into mechanical energy to drive the nacelle system.
  • Power is supplied to the integrated motor-generator through the battery, and the integrated motor-generator is used as an electric motor, and the blower is driven by the second steam turbine to supply energy to the temperature-changing device, and the vapor-state working medium in the liquid storage tank is extracted to convert the vapor-state working medium into
  • the temperature of the system working medium in the liquid storage tank keeps decreasing, and the temperature of the high-temperature steam output by the temperature-changing device continues to rise.
  • the liquid booster pump is turned on to make the system working medium become a high-pressure liquid;
  • the high-pressure liquid produced by the liquid pressurizing pump is heated by the first heat exchanger and the temperature changing device to drive the first steam turbine, and the first steam turbine drives the turbofan, and the turbofan sucks the external air into the nacelle of the aircraft, and enters all air in the nacelle of the aircraft.
  • the external air provides energy for the system working fluid through the first heat exchanger;
  • the system working fluid that absorbs heat energy flows to the temperature changing device, and after being further heated by the temperature changing device, it is transported to the first steam turbine to form a cycle;
  • the high-temperature steam generated by the temperature changing device drives the second steam turbine connected in parallel with the first steam turbine to rotate, which becomes the driving power of the temperature changing device, and at the same time drives the integrated motor generator to rotate, and the integrated motor generator acts as a generator to generate electricity for the battery. Supplementary power.
  • changing the first steam turbine engine to an electric motor can greatly reduce the difficulty of manufacturing the engine and improve reliability.
  • the electric motor is connected to the battery through the motor control device, accepts the battery and the second steam turbine, and integrates the motor generator The provided electric energy is driven to generate propulsion;
  • the battery supplies power to other devices in the aircraft that require electrical energy.
  • the invention has a simple structure, extracts heat energy from the air as the energy source of the first steam turbine and the aircraft through the circulation system composed of the temperature changing device, the first steam turbine and the heat exchanger, thereby driving the turbofan to rotate and absorbing more air as energy for the aircraft engine Source, the air flowing through the aircraft engine system provides thrust for the aircraft, the aircraft engine eliminates the dependence on fossil energy by extracting energy from the air, and the air flowing out of the aircraft engine cools down to form a low temperature environment, making the aircraft engine manufacturing materials Easier to solve, reduce production costs, eliminate carbon emissions and air pollution.
  • Fig. 1 is the schematic diagram of an embodiment of the air energy aircraft engine of the present invention
  • Fig. 2 is a schematic diagram of an embodiment of the temperature changing device of the present invention.
  • connection can also be a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediary, and it can be the internal communication of two components.
  • Fig. 1 is a schematic diagram of an embodiment of the air-energy aircraft engine of the present invention, as shown in Fig. 1, the air-energy aircraft engine comprises a main cabin system and a nacelle system, and the nacelle system is configured in the nacelle 13 of the aircraft Inside, it is used to collect air energy and send it into the main cabin system, and at the same time, the external air is inhaled from the front of the nacelle to be pressurized and then ejected from the rear of the nacelle, thereby generating thrust for the aircraft; the main cabin system is configured in the main cabin of the aircraft 20, used to convert low temperature energy into high temperature energy, and send high temperature energy into the nacelle system, and convert the high temperature energy into the nacelle into mechanical energy as the driving force of the nacelle system.
  • the method for the above-mentioned air energy vehicle engine to drive the aircraft comprises:
  • Step S11 collecting air energy through the nacelle system and sending it into the main cabin system, and at the same time, external air is inhaled from the front of the nacelle of the aircraft, pressurized, and then ejected from the rear of the nacelle, thereby generating thrust for the aircraft;
  • step S12 the low-temperature energy is converted into high-temperature energy through the main cabin system, and the high-temperature energy is sent into the nacelle system, and the high-temperature energy sent into the nacelle is converted into mechanical energy to drive the nacelle system.
  • the main cabin system includes a temperature changing device 2 for converting low-temperature steam into high-temperature steam;
  • the nacelle system includes a first steam turbine 23, a turbofan 24 And the first heat exchanger 1, the first steam turbine 1 is used to convert the high-temperature steam generated by the temperature changing device 2 into mechanical energy, and then drive the turbofan 24, and at the same time deliver the generated exhaust gas to the temperature changing device 2,
  • the turbofan 24 is used to draw the external air into the nacelle 13, the external air 14 entering the nacelle 13 provides heat energy for the system working fluid in the first heat exchanger through the first heat exchanger, and the system working fluid absorbing heat energy is transformed into a low temperature
  • the steam flows to the temperature changing device 2.
  • the main cabin system further includes a liquid storage tank 19, the liquid storage tank stores system working fluid, the liquid storage tank 19 has a gas end 19a and a liquid end 19b, the liquid storage tank The gas end 19 a provides low-temperature steam for the temperature changing device 2 , and the liquid end 19 b of the liquid storage tank sucks the low-temperature liquid in the temperature changing device 2 .
  • the system working fluid includes refrigerant, and the refrigerant is one or more of nitrogen, R23 and air.
  • the temperature changing device 2 has a low-pressure inlet port 2a, a low-pressure outlet port 2b, a high-pressure inlet port 2c and a high-pressure outlet port 2d, and the high-pressure outlet port 2d of the temperature changing device 2 is connected to the first steam turbine
  • the high-pressure inlet port 23a of 23 is connected
  • the low-pressure outlet port 23b of the first steam turbine 23 is connected with the low-pressure inlet port 2a of the temperature changing device 2
  • the high-temperature outlet port 1b of the first heat exchanger 1 is connected with the high-pressure inlet port 2c of the temperature changing device 2
  • the liquid end 19b of the liquid storage tank 19 communicates with the low pressure outlet port 2b of the temperature changing device 2
  • the gas end 19a of the liquid storage tank 19 communicates with the low pressure inlet port 2a of the temperature changing device 2 .
  • the temperature changing device includes a heat exchanger mechanism 200 and a blower 8, and the heat exchanging mechanism is provided with a low-pressure circuit input end 200a (also a low-pressure inlet end 2a of the temperature changing device), a low-pressure circuit output end 200b, high-pressure loop input 200c, and high-pressure loop output 200d (also the low-pressure outlet 2b of the temperature-variable device, the Rankine cycle is higher than the pressure of the high-pressure loop of the temperature-variable device, so the high-pressure loop is high pressure inside the temperature-variable device, relative to Rankine cycle is low pressure), a low-voltage circuit 6 is formed between the input end 200a of the low-voltage circuit and the output end 200b of the low-voltage circuit, a high-pressure circuit 5 is formed between the input end 200c of the high-voltage circuit and the output end 200d of the high-voltage circuit, and the inlet end of the blower 8 8a communicates with the low-pressure circuit of the heat
  • the low-temperature steam enters the low-pressure circuit of the heat exchange mechanism, and returns to the high-pressure circuit of the heat exchange mechanism after being pressurized and heated by the blower.
  • the heat exchange mechanism includes a second heat exchanger 3, a heat recovery heat exchanger 4 and a third heat exchanger 7, and the heat recovery heat exchanger 4, the third heat exchanger 7 and a blower 8 in series in sequence, and the second heat exchanger 3 and the third heat exchanger 7 are connected in parallel.
  • the low-temperature steam enters the low-pressure circuit from the input end 4a of the low-pressure circuit of the recuperator heat exchanger 4, and the low-temperature steam enters the blower through the inlet end of the blower 8 after being heated by the heat exchanger 4.
  • the blower pressurizes and heats up, high temperature and high pressure steam with higher temperature is formed.
  • the high-temperature and high-pressure steam is output from the outlet of the blower, part of which is sent to the third heat exchanger to heat the low-temperature steam in the low-pressure circuit, and the other part is sent to the second heat exchanger to heat the system delivered by the first heat exchanger Working fluid.
  • the high-temperature and high-pressure steam delivered by the blower is respectively cooled in the second heat exchanger 3 and the third heat exchanger 4 and then collected to the high-pressure circuit input end 4c of the recuperation heat exchanger and enters the high-pressure circuit of the recuperation heat exchanger for
  • the low-temperature steam heated in the low-pressure circuit of the regenerative heat exchanger is finally cooled to form a liquid working fluid, which is output through the output port 4d of the high-pressure circuit of the regenerative heat exchanger.
  • the temperature changing device further includes a temperature regulating valve 9, which is arranged in the high-pressure circuit of the temperature changing device, and is used to control the flow of high-temperature and high-pressure steam output by the blower between the second heat exchanger and the third heat exchanger.
  • a temperature regulating valve 9 which is arranged in the high-pressure circuit of the temperature changing device, and is used to control the flow of high-temperature and high-pressure steam output by the blower between the second heat exchanger and the third heat exchanger.
  • the temperature regulating valve is arranged on the high-pressure circuit between the third heat exchanger and the second heat exchanger to control the temperature regulating valve Satisfying the change of the flow rate ratio brought about by the change of the output temperature range of the second heat exchanger and the range of the raising temperature of the third heat exchanger.
  • the main cabin system further includes a second steam turbine 11, an integrated motor generator 12 and a storage battery 17; wherein, the second steam turbine 11 and the first steam turbine 23 are connected in parallel at variable temperature
  • the low-pressure inlet port 2a of the device 2 is connected with the high-pressure outlet port 2d of the temperature variable device;
  • the mechanical energy end 11m of the second steam turbine is mechanically connected with the blower 8 of the temperature variable device, and is used to drive the blower in the temperature variable device by mechanical energy
  • the electric energy terminal 11e is electrically connected to the storage battery through the integrated motor generator.
  • the second steam turbine When the second steam turbine is running, it drives the integrated motor generator and serves as a generator to supplement electric energy for the storage battery; when the storage battery drives the integrated motor generator, it acts as The electric motor generates mechanical energy to drive the blower in the temperature changing device.
  • the main cabin system further includes a second frequency converter 16, and the integrated motor generator is electrically connected to the storage battery through the second frequency converter.
  • the main cabin system also includes a regulating valve 15, which is used to regulate the flow rate of the gas working medium delivered by the temperature changing device to the second steam turbine, so as to adjust the rotation speed of the second steam turbine and the blower, thereby regulating the air flow of the aircraft. flight speed.
  • a regulating valve 15 which is used to regulate the flow rate of the gas working medium delivered by the temperature changing device to the second steam turbine, so as to adjust the rotation speed of the second steam turbine and the blower, thereby regulating the air flow of the aircraft. flight speed.
  • the main cabin system further includes a liquid booster pump 10, the low-pressure inlet port 10a of the liquid booster pump communicates with the liquid end of the liquid storage tank, and the high-pressure outlet port 10b of the liquid booster pump communicates with the second A low-temperature end 1a of a heat exchanger 1 is connected, and a liquid booster pump is connected to a storage battery at the same time.
  • the liquid pressurization pump is turned on through the battery, so that the system working medium is pressurized and sent to the first heat exchanger, and the liquid working medium is heated by the air sucked in the nacelle in the first heat exchanger
  • the vaporization is sent to the low-pressure inlet of the second heat exchanger, and then output from the high-pressure outlet of the second heat exchanger after being heated by the high-pressure circuit of the second heat exchanger.
  • Part of the gas working medium output from the second heat exchanger is sent to the first steam turbine, and the first steam turbine converts the received heat energy into mechanical energy to drive the turbofan, and at the same time, the exhaust gas generated by the first steam turbine is sent to the low-pressure circuit of the temperature change device
  • the low-pressure steam used as a temperature changing device that is, the exhaust gas produced by the first steam turbine is sent to the input end of the low-pressure circuit of the recuperator
  • another part of the gas working medium output from the second heat exchanger is sent to the second steam turbine, and the first The second steam turbine is used to convert heat energy into mechanical energy to drive the blower of the temperature variable device.
  • the exhaust gas generated by the second steam turbine is sent to the low-pressure circuit of the temperature variable device as low-pressure steam of the temperature variable device (that is, the exhaust gas generated by the second steam turbine is sent to the return low pressure loop input of the heat exchanger).
  • the main cabin system further includes a first frequency converter 18 , and the electric power end 10 e of the liquid booster pump is electrically connected to the storage battery 17 through the first frequency converter 18 .
  • the method for the above-mentioned air energy vehicle engine to drive the aircraft comprises:
  • Step S21 supply power to the integrated motor-generator through the storage battery, the integrated motor-generator is used as an electric motor, drive the blower through the second steam turbine to supply energy for the temperature changing device, extract the vapor state working medium in the liquid storage tank, and convert the vapor state
  • the working fluid is transformed into high-temperature steam, the temperature of the system working fluid in the liquid storage tank is continuously reduced, and the temperature of the high-temperature steam output by the temperature changing device is continuously rising.
  • the liquid booster pump is turned on, so that the system working fluid becomes high pressure liquid;
  • Step S22 the high-pressure liquid generated by the liquid booster pump is heated by the first heat exchanger and the temperature changing device to drive the first steam turbine, the first steam turbine drives the turbofan, and the turbofan sucks the external air into the nacelle of the aircraft and enters the nacelle of the aircraft
  • the external air inside provides energy for the system working fluid through the first heat exchanger;
  • Step S23 the system working fluid that absorbs heat energy flows to the temperature changing device, and after being further heated by the temperature changing device, it is transported to the first steam turbine to form a cycle;
  • Step S24 the high-temperature steam generated by the temperature changing device drives the second steam turbine connected in parallel with the first steam turbine to rotate, and becomes the driving force of the temperature changing device, and at the same time drives the integrated motor generator to rotate, and the integrated motor generator acts as a generator to generate electricity, thereby providing The storage battery supplements electric energy.
  • it also includes: providing power to other devices in the aircraft that require electric energy through the storage battery.
  • the nacelle system further includes a vectoring nozzle 22, which is arranged at the rear end of the nacelle of the aircraft.
  • the vectoring nozzle 22 can rotate 360 degrees, which can improve the operational performance of the aircraft and enhance the flexibility of the aircraft.
  • a thrust reverser 21 is provided at the exit of the vectoring nozzle 22, and the rotatable thrust reverser 21 is used for deceleration in the air or when landing.
  • turbofan 24 is close to an end of the nacelle 13 of the aircraft away from the thrust reverser 21 .
  • the heat exchange mechanism further includes a fourth heat exchanger 71, and the fourth heat exchanger is used to increase the high-pressure circuit and the low-pressure circuit of the high-temperature end of the third heat exchanger 7. temperature difference.
  • the low-pressure loop input end 4a of the recuperation heat exchanger 4 is the low-pressure inlet end 2a of the temperature changing device 2, and the low-pressure loop input end 4a of the recuperation heat exchanger 4 is respectively connected to the gas end 19a
  • the low-pressure outlet port 23b of the first steam turbine 23 communicates with the low-pressure outlet port 11b of the second steam turbine 11
  • the low-pressure circuit output port 4b of the recuperator heat exchanger 4 communicates with the low-pressure circuit input port 7a of the third heat exchanger 7, and the third
  • the low-pressure loop output end 7b of the heat exchanger 7 communicates with the low-pressure loop input end 71a of the fourth heat exchanger 71
  • the low-pressure loop output end 71b of the fourth heat exchanger 71 communicates with the inlet end 8a of the blower 8, and the blower 8
  • the outlet port 8b of the outlet port 8b communicates with the high-pressure circuit input port 71c of the fourth heat exchanger 71 and the high-pressure circuit input port 7
  • the high-pressure circuit input end 3c of the exchanger 3 is communicated, and the high-pressure circuit output end 3d of the second heat exchanger 3 is also communicated with the high-pressure circuit input end 4c of the heat recovery heat exchanger 4, and the heat recovery heat exchanger 4
  • the output port 4d of the high-pressure circuit is the low-pressure outlet port 2b of the temperature changing device 2
  • the output port 4d of the high-pressure circuit of the recuperator 4 communicates with the liquid end 19b of the liquid storage tank 19 and the low-pressure inlet port 10a of the liquid booster pump 10 respectively.
  • the second heat exchanger 3 also has a high-pressure inlet port 2c and a high-pressure outlet port 2d of the temperature changing device 2, and the high-pressure inlet port 2c of the second heat exchanger 3 communicates with the high-temperature outlet port 1b of the first heat exchanger 1 , the high-pressure outlet port 2d of the second heat exchanger 3 communicates with the high-pressure inlet port 23a of the first steam turbine 23 and communicates with the high-pressure inlet port 11a of the second steam turbine 11 through the regulating valve 15 .
  • the main shaft of the first steam turbine is a magnetic suspension bearing.
  • the method for the above-mentioned air energy vehicle engine to drive the aircraft comprises:
  • Step S31 starting the integrated motor generator 12 through the battery 17 and the first frequency converter 18, the integrated motor generator 12 is used as a motor, and the blower 8 of the temperature changing device is driven by the second steam turbine to extract the steam in the liquid storage tank 19
  • the working medium enters the low-pressure circuit 6 of the third heat exchanger 7 through the recuperation heat exchanger 4, heats up to obtain high-temperature steam, enters the low-pressure circuit 6 of the fourth heat exchanger 71, and further heats up; Pressurization; part of the pressurized high-temperature steam returns to the high-pressure circuit 5 of the temperature changing device 2 through the third heat exchanger 7, and part of the pressurized high-temperature steam passes through the fourth heat exchanger and the second heat exchanger 3 to return to the variable temperature
  • the high-pressure circuit 5 of the device 2 increases the temperature difference between the high-pressure circuit 5 and the low-pressure circuit 6 at the high-temperature end (high-pressure circuit input 7c) of the third heat exchanger 7 through the fourth heat exchanger 71, and the high-
  • Step S32 the high-pressure liquid generated by the liquid booster pump is heated by the first heat exchanger and the second heat exchanger to drive the first steam turbine, and the first steam turbine 23 drives the turbofan 24 to suck the external air 14 into the nacelle of the aircraft 13, the external air 14 entering the nacelle 13 of the aircraft provides heat energy for the system working fluid through the first heat exchanger 1;
  • Step S33 the system working fluid absorbing heat through step S32 flows through the first heat exchanger 1 and enters the high-pressure input end of the second heat exchanger to the high-pressure outlet end of the second heat exchanger 3, and is delivered to the first steam turbine 23 form a cycle;
  • Step S34 adjust the regulating valve 15 of the Rankine cycle, and the high-temperature steam generated by the second heat exchanger of the temperature changing device drives the second steam turbine 11 connected in parallel with the first steam turbine 23 to rotate under the action of high-temperature working fluid , become the driving power of the blower 8, and drive the integrated motor generator 12 to rotate and generate electricity, thereby supplementing electric energy for the battery 17, and providing electric energy for other devices in the aircraft that require power.
  • the temperature changing device 2 includes a plurality of heat exchange mechanisms and a plurality of blowers 8, one blower 8 is connected in series between the low pressure circuit 6 and the high pressure circuit 5 of a heat exchange mechanism, the first heat exchange mechanism
  • the second heat exchanger 3 communicates with the first heat exchanger 1, the first steam turbine 23 and the second steam turbine 11 respectively.
  • the fourth heat exchanger 71 of the previous heat exchange mechanism is used as the next heat exchange mechanism.
  • the second heat exchanger 3 of the mechanism so as to realize the series connection of multiple heat exchange mechanisms.
  • blower and/or the third heat exchanger and/or the fourth heat exchanger and/or the second heat exchanger are provided with an insulation layer.
  • the second heat exchanger 3 is connected to the heater of the first steam turbine 23 through a cooler to form a cooling-heater, and the low-pressure outlet port of the first steam turbine 23 is connected to the return of the temperature changing device 2
  • the low-pressure circuit input end of the heat exchanger 4 is connected, the high-temperature outlet end of the first heat exchanger 1 is connected with the low-temperature end of the cooling-heater (high-pressure inlet end), and the high-temperature end of the cooling-heater (high-pressure output end) It communicates with the high-pressure inlet port of the first steam turbine 23.
  • the third heat exchanger 7 is an isenthalpy heat exchanger
  • the fourth heat exchanger 71 is a temperature difference amplification heat exchanger
  • the system working fluid is pressurized by the liquid pressurizing pump 10, and after the cooling-heater is heated up, it becomes a high-temperature and high-pressure gas and enters the first steam turbine 23, and the high-temperature and high-pressure system working fluid entering the first steam turbine 23 generates isentropic expansion, thereby converting the thermal energy and potential energy of the system working fluid into mechanical energy, driving the turbofan 24 to rotate.
  • the rotational speed of the main shaft of the first steam turbine 23 and the turbofan 24 connected thereto increases gradually, and when the rotational speed of the turbofan 24 reaches the required rotational speed value, the start of the air energy aircraft engine is completed.
  • the turbofan 24 rotates at a high speed, and a strong suction is generated at the front end of the nacelle 13 of the aircraft to attract more air into the nacelle 13 of the aircraft, and the air flowing through the nacelle 13 of the aircraft passes through the first heat exchanger 1 While continuously supplying energy to the system, the discharge from the end of the nacelle 13 flowing through the aircraft generates powerful thrust to supply energy to the engine and push the aircraft forward.
  • the present invention obtains energy from the external air 14 entering in the nacelle 13 of the aircraft and uses it as the power of the engine, the temperature of the air discharged from the nacelle 13 of the aircraft is greatly reduced.
  • the external air 14 discharged from the nacelle 13 of the aircraft drops to about minus 170°C, and the resulting low temperature environment is compared to the high temperature environment produced by conventional engines burning fossil energy , It is easier to solve the engine material, which greatly reduces the production cost of the engine.
  • there is no high temperature effect at the end of the engine which greatly reduces the infrared radiation of the aircraft, which can effectively improve the stealth performance of the aircraft.
  • the invention includes that the engine includes a nacelle system and a main cabin system.
  • the nacelle system has a simple structure and a large thrust-to-weight ratio, and the gas turbine is replaced with a technically mature turboexpander, thereby reducing manufacturing difficulty.
  • a magnetic suspension bearing is used at the main shaft of the first steam turbine 23, so that the loss is very small when the first steam turbine 23 is in the working state of 20,000-60,000 revolutions.
  • the weight and volume of the main cabin system installed in the main cabin 20 of the aircraft are smaller than those of fossil fuels carried by existing aircraft, which increases the load capacity of the aircraft and is more practical.
  • the energy of the present invention is derived from the external air 14, so the flight cost is low and there is no range limitation.
  • nitrogen is used as the working fluid of the system
  • the inlet pressure is 1.2 MPa
  • the exhaust pressure is 0.2 MPa.
  • the inlet temperature is 10 degrees
  • the enthalpy drop generated is 120 kJ/kg
  • the generated temperature Reduced to 120K that is, the exhaust temperature is minus 110 degrees.
  • the temperature difference between the external air 14 flowing into the nacelle 13 of the aircraft and the first heat exchanger 1 is 20K.
  • the temperature drop of air 14 is 100 degrees, when the system working fluid flow is equal to the flow of external air 14 (ignoring the specific gravity difference between nitrogen and external air 14), when the external air 14 of 30 degrees flows into the nacelle 13 of the aircraft, it flows out of the aircraft
  • the temperature of the external air 14 of the nacelle 13 will drop to minus 70 degrees, so the first steam turbine 23 obtains an energy of 100kJ/kg.
  • the flow rate of the external air 14 is 300kg/s
  • the Boeing 737 single-engine take-off thrust is 10 tons, and the above-mentioned is the maximum take-off thrust that the air energy aircraft engine of the present invention and the fuel aeroengine may obtain under the same 300kg/s air intake rate. It can be seen that the air energy aircraft The thrust produced by the engine is far greater than that of the fuel aero-engine (the energy M(V 9 -V 0 ) 2 /2 carried away by the jet flow is ignored here).
  • the air density drops to 1/3 of that on the ground, and the energy obtained by the first steam turbine 231 of the air energy aircraft engine also drops to 1/3 of the ground, and the cruising speed of the plane is Mach 0.8.
  • the cruising thrust of the Boeing 737 is two tons. It can be seen that during cruising, the thrust of the air-energy aircraft engine is also greater than that of the fuel-fueled aircraft engine (the energy M(V 9 -V 0 ) 2 /2 taken away by the jet airflow is ignored here).
  • the air energy engine is an independent closed cycle system and is not affected by the height of the ground.
  • the air density drops to 1/3 of the ground, and the turbofan 24 operates If the power is reduced, the speed of the first steam turbine 23 will increase to 3 times that of the sea level, and the flow rate of the external air 14 at the turbofan 24 is proportional to the rotational speed of the turbofan 24.
  • the air-energy aircraft engine has a strong thrust potential.
  • ordinary civil aviation airliners with improved designs can work at supersonic speeds.
  • the cruise The speed can reach more than Mach 3, especially because the engine temperature of the air-powered aircraft is very low, and magnetic suspension bearings can be used. Therefore, the limiting factors for increasing the engine speed are only the linear velocity of the turbofan 24 made of composite materials, and the flying height of the aircraft. It can also reach 30,000 meters.
  • changing the first steam turbine engine to an electric engine can greatly reduce the difficulty of manufacturing the engine and improve reliability.
  • the electric engine is connected to the battery through the motor control device, and the battery and the second steam turbine , the electric energy provided by the integrated motor-generator is driven to generate propulsion.
  • the invention can eliminate the dependence on fossil energy, increase the speed of the aircraft, avoid air pollution, reduce the manufacturing difficulty and cost of the engine.
  • the main cabin 20 of aircraft and the nacelle 13 of aircraft are not absolute, and the main cabin 20 of aircraft comprises aircraft main body and wing, refers to the space that parts can be installed except nacelle, if necessary When they are put together, as long as the basic structure remains unchanged, the inventiveness of the present invention is still not affected.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un moteur d'aéronef à énergie pneumatique, comprenant un système pour cabine principale et un système pour nacelle. Le système pour nacelle est configuré dans une nacelle (13) de l'aéronef pour collecter de l'énergie pneumatique et pour envoyer celle-ci au système pour cabine principale, tandis que de l'air externe est aspiré depuis l'avant de la nacelle à des fins de mise sous pression puis est éjecté à partir de l'arrière de la nacelle, pour ainsi générer une poussée au niveau d'un aéronef ; le système pour cabine principale est configuré dans une cabine principale (20) de l'aéronef pour convertir de l'énergie à basse température en énergie à haute température et pour envoyer l'énergie à haute température dans le système pour nacelle, et l'énergie à haute température est convertie en énergie mécanique pour servir de force d'entraînement pour le système pour nacelle. L'invention concerne également un procédé d'entraînement d'un aéronef. Le moteur peut éliminer la dépendance liée à l'énergie fossile, de telle sorte que la vitesse de l'aéronef est améliorée, la pollution de l'air est évitée, la difficulté de fabrication du moteur est réduite, et les coûts sont réduits.
PCT/CN2022/076888 2021-09-18 2022-02-18 Moteur d'aéronef à énergie pneumatique et procédé d'entraînement d'aéronef WO2023040183A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CN202122295733.0 2021-09-18
CN202111112192.1A CN114248930A (zh) 2021-09-18 2021-09-18 空气能飞行器发动机及驱动飞行器的方法
CN202111112192.1 2021-09-18
CN202122295733 2021-09-18

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WO2023040183A1 true WO2023040183A1 (fr) 2023-03-23

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140345292A1 (en) * 2013-05-22 2014-11-27 General Electric Company Return fluid air cooler system for turbine cooling with optional power extraction
CN109989833A (zh) * 2019-04-24 2019-07-09 北京航空航天大学 一种用于高超声速飞行器或发动机的综合热管理系统
CN111779576A (zh) * 2020-07-13 2020-10-16 中国航空发动机研究院 一种组合式推进装置、系统及控制方法
CN112319799A (zh) * 2020-11-03 2021-02-05 谭成刚 无翼飞行器
CN114248930A (zh) * 2021-09-18 2022-03-29 成都佳灵绿色能源有限责任公司 空气能飞行器发动机及驱动飞行器的方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140345292A1 (en) * 2013-05-22 2014-11-27 General Electric Company Return fluid air cooler system for turbine cooling with optional power extraction
CN109989833A (zh) * 2019-04-24 2019-07-09 北京航空航天大学 一种用于高超声速飞行器或发动机的综合热管理系统
CN111779576A (zh) * 2020-07-13 2020-10-16 中国航空发动机研究院 一种组合式推进装置、系统及控制方法
CN112319799A (zh) * 2020-11-03 2021-02-05 谭成刚 无翼飞行器
CN114248930A (zh) * 2021-09-18 2022-03-29 成都佳灵绿色能源有限责任公司 空气能飞行器发动机及驱动飞行器的方法

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