Energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery

Abstract

The present invention discloses an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, belonging to the field of aircraft airborne electromechanical systems. The present invention utilizes the recovered energy to drive a high-boost-ratio air centrifugal compressor to suck in external ram air and compress, heat up and boost the pressure to meet the requirements of the environmental control system for refrigeration, cabin pressurization, etc.; uses the cabin exhaust gas as the cold source of the regenerative heat exchanger to pre-cool the high-temperature and high-pressure gas; uses the cooling turbine to drive the compressor to boost the pressure of the oxygen-rich gas separated by the fuel tank inerting system to achieve cabin oxygenation. The present invention adopts a coupling method to fully recover and utilize the heat of the thermal protection system, without bleeding air from the engine, reducing the aircraft's compensation loss and improving the energy utilization rate; fully recovers and utilizes the waste gas discharged from the cabin, reduces the amount of ram air, reduces the aircraft drag and lightens the weight of the heat exchanger; the environmental control system adopts a three-stage self-cleaning filter, which can effectively prevent the deposition of virus suspensions and prevent the spread of epidemics.

Description

Technical Field

[0001] The present invention relates to the technical field of airborne electromechanical technology for aircraft, and particularly to an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery. Background Art

[0002] During the flight of an aircraft, due to the strong compression and friction of air, intense aerodynamic heat is generated. At the same time, the high heat loads of the airborne avionics equipment and airborne electromechanical equipment of new-generation aircraft will also increase significantly, making the design of aircraft thermal protection face severe challenges. Traditional thermal protection systems usually use high-temperature and corrosion-resistant composite materials for heat dissipation. At the same time, some heat will enter the aircraft body through the composite material structure, which not only causes a large amount of heat waste but also poses higher requirements for the thermal management system inside the aircraft body.

[0003] Meanwhile, the flight safety of aircraft has always been a topic of social concern, and the safety of the aircraft fuel tank is one of the important guarantees for the normal flight of the aircraft. Corresponding measures must be taken to prevent the explosion of the aircraft fuel tank. At present, the most economical, efficient, and feasible means is the airborne fuel tank inerting technology. The gas is divided into nitrogen-rich gas and oxygen-rich gas through an air separation module. The nitrogen-rich gas is introduced into the fuel tank to reduce the oxygen concentration in the gas phase space of the fuel tank and achieve inerting protection of the fuel tank. The oxygen-rich gas is sent into the cockpit after being pressurized by a compressor to increase the oxygen content. However, traditional aircraft environmental control systems, fuel tank inerting systems, etc. are relatively independent, and the energy of each system is not centrally managed and reasonably distributed, resulting in a large amount of energy waste.

[0004] Most of the existing aircraft environmental control systems and fuel tank inerting systems draw air from the aircraft engine, and engine air extraction will bring a series of disadvantages. On the one hand, engine air extraction will affect the flight performance of the aircraft and cause an increase in fuel compensation loss. On the other hand, high-temperature and high-pressure gas entering the fuel tank inerting system may cause spontaneous combustion of the fuel, ultimately leading to fuel tank explosion. Summary of the Invention

[0005] In view of the technical defects involved in the background art, the present invention provides an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, which uses the recovered energy to drive a high-boost-ratio air centrifugal compressor to suck in external ram air and compress, heat up, and boost it to meet the requirements of the environmental control system for refrigeration, cockpit pressurization, etc.

[0006] The present invention adopts the following technical solutions:

[0007] The present invention discloses an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, which includes a phase change heat storage device, a first cooling turbine, a first condenser, a pump, a high-boost-ratio air centrifugal compressor, a regenerative heat exchanger, a secondary heat exchanger, a three-way valve, an air separation module, a control valve, a flame arrester, a fuel tank, an air centrifugal compressor, a fan, a recuperator, a second cooling turbine, a second condenser, a water separator, a self-cleaning primary air filter, a gas mixing chamber, a self-cleaning medium-efficiency air filter, a self-cleaning high-efficiency air filter, a cockpit, and a self-cleaning medium-efficiency air filter return air device;

[0008] The phase change heat storage device recovers the heat of the thermal protection system, and is successively connected to the first cooling turbine, the first condenser, the pump, and finally returns to the phase change heat storage device to form a closed-loop system;

[0009] The inlet of the high-boost-ratio air centrifugal compressor is connected to the ram air outside the airframe, and the outlet is successively connected to the hot side channel of the regenerative heat exchanger and the hot side channel of the secondary heat exchanger;

[0010] One end of the hot side channel of the secondary heat exchanger is connected to the three-way valve. The gas after passing through the three-way valve is divided into two paths. One path is connected to the gas inlet of the air separation module, and the other path is successively connected to the hot channel side of the recuperator, the hot channel side of the second condenser, and the water separator;

[0011] The liquid water separated by the water separator is sprayed onto the inlet of the cold channel side of the secondary heat exchanger; the outlet of the water separator is successively connected to the cold channel side of the recuperator, the second cooling turbine, the cold channel side of the second condenser, the self-cleaning primary air filter, and the fresh air inlet of the gas mixing chamber;

[0012] The mixed gas in the gas mixing chamber is sent into the cockpit after passing through the self-cleaning medium-efficiency air filter and the self-cleaning high-efficiency air filter; the exhaust air channel of the cockpit is connected to the cold channel side of the regenerative heat exchanger; the return air channel of the cockpit is successively connected to the self-cleaning medium-efficiency air filter return air device and the return air inlet of the gas mixing chamber;

[0013] The first cooling turbine and the high-boost-ratio air centrifugal compressor are coaxially connected, and the output power of the first cooling turbine drives the high-boost-ratio air centrifugal compressor; the fan, the air centrifugal compressor, and the second cooling turbine are coaxially connected, and the output power of the second cooling turbine drives the fan and the air centrifugal compressor;

[0014] The air separation module includes a gas inlet, a rich oxygen gas outlet, and a rich nitrogen gas outlet. The air separation module separates the gas entering the gas inlet into rich oxygen gas and rich nitrogen gas; the rich oxygen gas outlet is successively connected to the air centrifugal compressor and the pressurized oxygen supply inlet of the gas mixing chamber; the rich nitrogen gas outlet is successively connected to the control valve, the flame arrester, and the fuel tank;

[0015] One end of the cold channel side of the regenerative heat exchanger is connected to the cabin exhaust, and the other end communicates with the outside; one end of the cold channel side of the secondary heat exchanger is connected to the ram air, and the other end is connected to the fan and communicates with the outside; the fan is used to suck the ram air and discharge it outside the aircraft body;

[0016] The mixed gas outlet of the gas mixing chamber is successively connected to a self-cleaning medium-efficiency air filter and a self-cleaning high-efficiency air filter, and the filtered clean gas is sent into the cabin;

[0017] The gas mixing chamber includes a fresh air inlet, a pressurized oxygen supply inlet, a return air inlet and a mixed gas outlet. The fresh air inlet is connected to the outlet of the self-cleaning primary air filter, the pressurized oxygen supply inlet is connected to the outlet of the air centrifugal compressor, the return air inlet is connected to the self-cleaning medium-efficiency air filter return device, and the mixed gas outlet is connected to the inlet of the self-cleaning medium-efficiency air filter.

[0018] A working method of an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery. Heat recovery is realized based on a phase change heat storage device, and the recovered energy is used to drive a high-boost-ratio air centrifugal compressor to meet the system's air extraction transportation and refrigeration requirements. Air separation and nitrogen generation and oxygen supply are realized based on an air separation module. Air is separated into nitrogen-rich gas and oxygen-rich gas. The nitrogen-rich gas enters the fuel tank to realize inerting protection of the fuel tank, and the oxygen-rich gas is pressurized by an air centrifugal compressor to realize cabin oxygen enrichment. The environmental control system completes the clean air filtration process based on the three-stage self-cleaning filtration of the self-cleaning primary air filter, the self-cleaning medium-efficiency air filter and the self-cleaning high-efficiency air filter.

[0019] Preferably, the heat recovery process is specifically as follows: The heat of the thermal protection system is conducted to the phase change heat storage device. The liquid refrigerant transported by the pump enters the phase change heat storage device, absorbs a large amount of heat and becomes high-temperature and high-pressure steam. Subsequently, it enters the first cooling turbine to expand and do work. The expanded steam is condensed into liquid refrigerant by the first condenser, and then the liquid refrigerant is transported to the phase change heat storage device by the pump again. Such a cycle is carried out to realize the continuous recovery and utilization of heat;

[0020] Preferably, the air bleeding and refrigeration process is as follows: Ram air first enters a high-boost-ratio centrifugal compressor driven by a first cooling turbine to be heated and pressurized. The high-temperature and high-pressure gas supplied by the high-boost-ratio centrifugal compressor is precooled by a regenerative heat exchanger, and the cold source is provided by the cabin exhaust. The gas cooled by the regenerative heat exchanger is further cooled by a secondary heat exchanger, and the cold source is provided by the ram air sucked by the fan. The gas cooled by the secondary heat exchanger is divided into two paths by a three-way valve. One path enters the air separation module of the fuel tank inerting system, and the other path enters the inlet of the hot side channel of the condenser through the hot side channel of the recuperator. After being cooled by the cold air at the outlet of the second cooling turbine in the condenser, the liquid water is separated by a water separator, and the separated liquid water is sprayed at the inlet of the ram air on the cold channel side of the secondary heat exchanger. The gas enters the second cooling turbine through the cold side channel of the recuperator to expand and cool down, and then enters the inlet of the cold side channel of the condenser. The gas passing through the condenser passes through a self-cleaning primary filter, and the gas after primary filtration enters the gas mixing chamber;

[0021] Preferably, the air separation and nitrogen generation and oxygen supply process is as follows: The other path of the gas separated by the three-way valve enters the air separation module of the fuel tank inerting system. The gas is separated into oxygen-rich gas and nitrogen-rich gas. The oxygen-rich gas is pressurized by an air centrifugal compressor driven by the output power of the second cooling turbine, and then enters the gas mixing chamber; The nitrogen-rich gas passes through a control valve and a flame arrester and enters the fuel tank to reduce the oxygen concentration in the gas phase space of the fuel tank, realizing the inerting protection of the fuel tank;

[0022] Preferably, the clean air filtration process is as follows: The oxygen-rich gas pressurized by the air centrifugal compressor, the gas initially filtered by the self-cleaning primary air filter, and the cabin return air filtered by the self-cleaning medium-efficiency air filtration return device are mixed in the gas mixing chamber. The mixed gas is secondarily filtered by the self-cleaning medium-efficiency air filter, and finally sent into the cabin through the self-cleaning high-efficiency filter. By circulating in this way, the pollution in the clean space of the cabin can be controlled at a relatively stable level within a certain period of time.

[0023] Compared with the prior art, the present invention adopting the above technical solutions has the following beneficial effects:

[0024] 1) The present invention solves the problems that traditional aircraft need to bleed air from the engine, resulting in reduced performance and increased fuel compensation loss. The energy recovered by the heat recovery system is used to drive a high-boost-ratio air centrifugal compressor to suck external ram air and compress, heat and pressurize it to meet the requirements of the environmental control system for refrigeration, cabin pressurization, etc. There is no need to bleed air from the engine, reducing the aircraft's compensation loss, improving the energy utilization efficiency, and saving energy.

[0025] 2) The present invention solves the problems that the primary heat exchanger of traditional aircraft requires ram air as a cold source, resulting in an increase in equipment weight and aircraft drag. By using the cabin exhaust gas as the cold source of the regenerative heat exchanger, it pre-cools the high-temperature and high-pressure gas, fully recovers and utilizes the waste gas discharged from the cabin, reduces the amount of ram air, decreases the aircraft drag, and lightens the weight of the heat exchanger.

[0026] 3) The present invention solves the problem that traditional aircraft need to add a separate compressor to boost the pressure of oxygen-rich gas. By using the cooling turbine in the environmental control system to drive the compressor, it increases the pressure of the oxygen-rich gas separated from the fuel tank inerting system to achieve cabin oxygenation and lighten the equipment weight.

[0027] 4) The present invention solves the problem of possible cross-infection of viruses in the cabin of traditional aircraft. The environmental control system adopts a three-stage self-cleaning filter, which can effectively prevent the deposition of virus suspensions, prevent the spread of epidemics, and ensure the health and safety of the crew. Brief Description of the Drawings

[0028] Figure 1 It is a schematic diagram of an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery according to the present invention.

[0029] In the figure, 1 - phase change heat storage device, 2 - first cooling turbine, 3 - first condenser, 4 - pump, 5 - high-boost-ratio air centrifugal compressor, 6 - regenerative heat exchanger, 7 - secondary heat exchanger, 8 - three-way valve, 9 - air separation module, 10 - control valve, 11 - flame arrester, 12 - fuel tank, 13 - air centrifugal compressor, 14 - fan, 15 - recuperator, 16 - second cooling turbine, 17 - second condenser, 18 - water separator, 19 - self-cleaning primary air filter, 20 - gas mixing chamber, 21 - self-cleaning intermediate air filter, 22 - self-cleaning high-efficiency air filter, 23 - cabin, 24 - self-cleaning intermediate air filter return air device. Detailed Description of the Preferred Embodiments

[0030] The following further details the technical solutions in the embodiments of the present invention with reference to the drawings:

[0031] The present invention can be implemented in many different embodiments, and the described embodiments are only a part of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] Such as Figure 1As shown in the figure, the present invention discloses an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, which includes a phase change heat storage device 1, a first cooling turbine 2, a first condenser 3, a pump 4, a high-boost-ratio air centrifugal compressor 5, a regenerative heat exchanger 6, a secondary heat exchanger 7, a three-way valve 8, an air separation module 9, a control valve 10, a flame arrester 11, a fuel tank 12, an air centrifugal compressor 13, a fan 14, a recuperator 15, a second cooling turbine 16, a second condenser 17, a water separator 18, a self-cleaning primary air filter 19, a gas mixing chamber 20, a self-cleaning medium-efficiency air filter 21, a self-cleaning high-efficiency air filter 22, a cockpit 23, and a self-cleaning medium-efficiency air filtering return air device 24;

[0033] The phase change heat storage device 1 recovers the heat of the thermal protection system, is sequentially connected to the first cooling turbine 2, the first condenser 3, and the pump 4, and finally returns to the phase change heat storage device 1 to form a closed-loop system;

[0034] The inlet of the high-boost-ratio air centrifugal compressor 5 is connected to the ram air outside the airframe, and the outlet is sequentially connected to the hot-side channel of the regenerative heat exchanger 6 and the hot-side channel of the secondary heat exchanger 7;

[0035] One end of the hot-side channel of the secondary heat exchanger 7 is connected to the three-way valve 8. The gas after passing through the three-way valve 8 is divided into two paths. One path is connected to the gas inlet of the air separation module 9, and the other path is sequentially connected to the hot-channel side of the recuperator 15, the hot-channel side of the second condenser 17, and the water separator 18;

[0036] The liquid water separated by the water separator 18 is sprayed at the inlet of the cold-channel side of the secondary heat exchanger 7. The outlet of the water separator 18 is sequentially connected to the cold-channel side of the recuperator 15, the second cooling turbine 16, the cold-channel side of the second condenser 17, the self-cleaning primary air filter 19, and the fresh air inlet of the gas mixing chamber 20;

[0037] The mixed gas in the gas mixing chamber 20 is sent into the cockpit after passing through the self-cleaning medium-efficiency air filter 21 and the self-cleaning high-efficiency air filter 22. The exhaust air channel of the cockpit 23 is connected to the cold-channel side of the regenerative heat exchanger 6. The return air channel of the cockpit 23 is sequentially connected to the self-cleaning medium-efficiency air filtering return air device 24 and the return air inlet of the gas mixing chamber 20;

[0038] The first cooling turbine 2 and the high-boost-ratio air centrifugal compressor 5 are coaxially connected, and the output power of the first cooling turbine 2 drives the high-boost-ratio air centrifugal compressor 5; the fan 14, the air centrifugal compressor 13, and the second cooling turbine 16 are coaxially connected, and the output power of the second cooling turbine 16 drives the fan 14 and the air centrifugal compressor 13;

[0039] The air separation module 9 includes a gas inlet, an oxygen-rich gas outlet, and a nitrogen-rich gas outlet. The air separation module 9 separates the gas entering the gas inlet into oxygen-rich gas and nitrogen-rich gas. The oxygen-rich gas outlet is sequentially connected to the air centrifugal compressor 13 and the pressurized oxygen supply inlet of the gas mixing chamber 20. The nitrogen-rich gas outlet is sequentially connected to the control valve 10, the flame arrester 11, and the fuel tank 12.

[0040] One end of the cold channel side of the regenerative heat exchanger 6 is connected to the cabin exhaust gas, and the other end communicates with the outside. One end of the cold channel side of the secondary heat exchanger 7 is connected to the ram air, and the other end is connected to the fan 14 and communicates with the outside. The fan 14 is used to suck the ram air and discharge it outside the aircraft body.

[0041] The mixed gas outlet of the gas mixing chamber 20 is sequentially connected to the self-cleaning medium-efficiency air filter 21 and the self-cleaning high-efficiency air filter 22, and the filtered clean gas is sent into the cabin 23.

[0042] The gas mixing chamber 20 includes a fresh air inlet, a pressurized oxygen supply inlet, a return air inlet, and a mixed gas outlet. The fresh air inlet is connected to the outlet of the self-cleaning primary air filter 19. The pressurized oxygen supply inlet is connected to the outlet of the air centrifugal compressor 13. The return air inlet is connected to the self-cleaning medium-efficiency air filter return air device 24. The mixed gas outlet is connected to the inlet of the self-cleaning medium-efficiency air filter 21.

[0043] The system realizes heat recovery based on the phase change heat storage device 1, and uses the recovered energy to drive the high-boost-ratio air centrifugal compressor 5 to meet the system's air intake transportation and refrigeration requirements. Based on the air separation module 9, air separation and nitrogen production and oxygen supply are realized. The air is separated into nitrogen-rich gas and oxygen-rich gas. The nitrogen-rich gas enters the fuel tank 12 to realize the inerting protection of the fuel tank. The oxygen-rich gas is pressurized by the air centrifugal compressor 13 to increase the oxygen content in the cabin 23. The environmental control system completes the clean air filtration process based on the three-stage self-cleaning filtration of the self-cleaning primary air filter 19, the self-cleaning medium-efficiency air filter 21, and the self-cleaning high-efficiency air filter 22.

[0044] The present invention discloses a working method of an energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery. The process is as follows:

[0045] 1) Heat recovery process

[0046] The heat of the thermal protection system is conducted to the phase change heat storage device 1. The liquid refrigerant transported by the pump 4 enters the phase change heat storage device 1, absorbs a large amount of heat and becomes high-temperature and high-pressure steam, and then enters the first cooling turbine 2 to expand and do work. The expanded steam is condensed into liquid refrigerant by the first condenser 3, and the liquid refrigerant is transported to the phase change heat storage device 1 by the pump 4 again. This cycle is repeated to realize the continuous recovery and utilization of heat.

[0047] 2) Bleed air transportation and refrigeration process

[0048] Ram air first enters the high-boost-ratio centrifugal compressor 5 driven by the first cooling turbine 2 to increase in temperature and pressure. The high-temperature and high-pressure gas supplied by the high-boost-ratio centrifugal compressor 5 is precooled by the regenerative heat exchanger 6, with the cold source provided by the cabin exhaust. The gas cooled by the regenerative heat exchanger 6 is further cooled by the secondary heat exchanger 7, with the cold source provided by the ram air suctioned by the fan 14. The gas cooled by the secondary heat exchanger 7 is divided into two paths by the three-way valve 8. One path enters the air separation module 9 of the fuel tank inerting system, and the other path enters the inlet of the hot side channel of the condenser 16 through the hot side channel of the recuperator 15. After being cooled by the cold air at the outlet of the second cooling turbine 16 in the condenser 16, the liquid water is separated by the water separator 18, and the separated liquid water is sprayed at the ram air inlet on the cold channel side of the secondary heat exchanger 7. The gas enters the second cooling turbine 16 through the cold side channel of the recuperator 16 to expand and decrease in temperature, and then enters the inlet of the cold side channel of the condenser 16. The gas passing through the condenser 16 passes through the self-cleaning primary filter 19, and the gas after primary filtration enters the gas mixing chamber 20.

[0049] 3) Air separation and nitrogen generation and oxygen supply process

[0050] The other path of the gas separated by the three-way valve 8 enters the air separation module 9 of the fuel tank inerting system. The gas is separated into oxygen-rich gas and nitrogen-rich gas. The oxygen-rich gas is pressurized by the air centrifugal compressor 13 driven by the output power of the second cooling turbine 16, and then enters the gas mixing chamber 20. The nitrogen-rich gas passes through the control valve 10 and the flame arrester 11 and enters the fuel tank 12 to reduce the oxygen concentration in the gas phase space of the fuel tank, realizing the inerting protection of the fuel tank.

[0051] 4) Clean air filtration process

[0052] The oxygen-rich gas pressurized by the air centrifugal compressor 13, the gas initially filtered by the self-cleaning primary air filter 19, and the cabin return air filtered by the self-cleaning medium-effect air filtration return air device 24 are mixed in the gas mixing chamber 20. The mixed gas is secondarily filtered by the self-cleaning medium-effect air filter 21, and finally sent into the cabin 23 through the self-cleaning high-efficiency filter 22. By circulating in this way, the pollution in the clean space of the cabin can be controlled at a relatively stable level within a certain period of time.

[0053] Those skilled in the art can understand that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as the general understanding of those of ordinary skill in the art to which the present invention pertains. It should also be understood that terms such as those defined in a general dictionary should be understood to have a meaning consistent with their meaning in the context of the prior art, and will not be interpreted in an idealized or overly formal sense unless defined as such herein.

[0054] The specific embodiments described above further elaborate on the object, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only for the specific embodiments of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. An energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, characterized in that, It includes a phase change heat storage device (1), a first cooling turbine (2), a first condenser (3), a pump (4), a high-boost-ratio air centrifugal compressor (5), a regenerative heat exchanger (6), a secondary heat exchanger (7), a three-way valve (8), an air separation module (9), a control valve (10), a flame arrester (11), a fuel tank (12), an air centrifugal compressor (13), a fan (14), a recuperator (15), a second cooling turbine (16), a second condenser (17), a water separator (18), a self-cleaning primary air filter (19), a gas mixing chamber (20), a self-cleaning medium-efficiency air filter (21), a self-cleaning high-efficiency air filter (22), a cockpit (23), and a self-cleaning medium-efficiency air filter return air device (24); The phase change heat storage device (1) recovers the heat of the thermal protection system and is sequentially connected to the first cooling turbine (2), the first condenser (3), the pump (4), and finally returns to the phase change heat storage device (1) to form a closed-loop system; The inlet of the high-boost-ratio air centrifugal compressor (5) is connected to the ram air outside the airframe, and the outlet is sequentially connected to the hot side channel of the regenerative heat exchanger (6) and the hot side channel of the secondary heat exchanger (7); One end of the hot side channel of the secondary heat exchanger (7) is connected to the three-way valve (8). The gas after passing through the three-way valve (8) is divided into two paths. One path is connected to the gas inlet of the air separation module (9), and the other path is sequentially connected to the hot channel side of the recuperator (15), the hot channel side of the second condenser (17), and the water separator (18); The liquid water separated by the water separator (18) is sprayed at the inlet of the cold channel side of the secondary heat exchanger (7). The outlet of the water separator (18) is sequentially connected to the cold channel side of the recuperator (15), the second cooling turbine (16), the cold channel side of the second condenser (17), the self-cleaning primary air filter (19), and the fresh air inlet of the gas mixing chamber (20); The mixed gas in the gas mixing chamber (20) is sent into the cockpit after passing through the self-cleaning medium-efficiency air filter (21) and the self-cleaning high-efficiency air filter (22). The exhaust air channel of the cockpit (23) is connected to the cold channel side of the regenerative heat exchanger (6). The return air channel of the cockpit (23) is sequentially connected to the self-cleaning medium-efficiency air filter return air device (24) and the return air inlet of the gas mixing chamber (20); The first cooling turbine (2) and the high-boost-ratio air centrifugal compressor (5) are coaxially connected, and the output power of the first cooling turbine (2) drives the high-boost-ratio air centrifugal compressor (5). The fan (14), the air centrifugal compressor (13), and the second cooling turbine (16) are coaxially connected, and the output power of the second cooling turbine (16) drives the fan (14) and the air centrifugal compressor (13).

2. The energy-saving and clean air-conditioning and fuel tank inerting coupling system based on heat recovery according to claim 1, wherein The air separation module (9) includes a gas inlet, an oxygen-rich gas outlet, and a nitrogen-rich gas outlet. The air separation module (9) separates the gas entering the gas inlet into oxygen-rich gas and nitrogen-rich gas. The oxygen-rich gas outlet is sequentially connected to the air centrifugal compressor (13) and the pressurized oxygen supply inlet of the gas mixing chamber (20). The nitrogen-rich gas outlet is sequentially connected to the control valve (10), the flame arrester (11), and the fuel tank (12).

3. The energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery according to claim 1, wherein One end of the cold channel side of the regenerative heat exchanger (6) is connected to the cabin exhaust, and the other end communicates with the outside. One end of the cold channel side of the secondary heat exchanger (7) is connected to the ram air, and the other end is connected to the fan (14) and communicates with the outside. The fan (14) is used to suck the ram air and discharge it outside the aircraft body.

4. The energy-saving and clean air-conditioning and fuel tank inerting coupling system based on heat recovery according to claim 1, characterized in that The mixed gas outlet of the gas mixing chamber (20) is sequentially connected to the self-cleaning medium-efficiency air filter (21) and the self-cleaning high-efficiency air filter (22), and the filtered clean gas is sent into the cabin (23).

5. The energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery according to claim 1, wherein The gas mixing chamber (20) includes a fresh air inlet, a pressurized oxygen supply inlet, a return air inlet, and a mixed gas outlet. The fresh air inlet is connected to the outlet of the self-cleaning primary air filter (19), the pressurized oxygen supply inlet is connected to the outlet of the air centrifugal compressor (13), the return air inlet is connected to the self-cleaning medium-efficiency air filter return air device (24), and the mixed gas outlet is connected to the inlet of the self-cleaning medium-efficiency air filter (21).

6. The working method of the energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery, according to the system described in claim 1, characterized in that, This system realizes heat recovery based on the phase change heat storage device (1), uses the recovered energy to drive the high-boost-ratio air centrifugal compressor (5) to meet the system's air extraction transportation and refrigeration requirements, realizes air separation and nitrogen production and oxygen supply based on the air separation module (9), separates the air into nitrogen-rich gas and oxygen-rich gas, the nitrogen-rich gas enters the fuel tank (12) to realize inerting protection of the fuel tank, and the oxygen-rich gas is pressurized by the air centrifugal compressor (13) to realize oxygen enrichment in the cabin (23). The environmental control system completes the clean air filtration process based on the three-stage self-cleaning filtration of the self-cleaning primary air filter (19), the self-cleaning medium-efficiency air filter (21), and the self-cleaning high-efficiency air filter (22).

7. The working method of the energy-saving and clean air conditioning and fuel tank inerting coupling system based on heat recovery according to claim 6, characterized in that, The specific heat recovery process is as follows: The heat of the thermal protection system is conducted to the phase change heat storage device (1). The liquid refrigerant transported by the pump (4) enters the phase change heat storage device (1), absorbs a large amount of heat and becomes high-temperature and high-pressure steam, and then enters the first cooling turbine (2) to expand and do work. The expanded steam is condensed into liquid refrigerant by the first condenser (3), and the liquid refrigerant is transported to the phase change heat storage device (1) by the pump (4) again. This cycle is repeated to continuously recover and utilize the heat.

8. The working method of the energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery according to claim 6, characterized in that, The specific air extraction transportation and refrigeration process is as follows: Ram air first enters the high-boost-ratio centrifugal compressor (5) driven by the first cooling turbine (2) to be heated and pressurized. The high-temperature and high-pressure gas supplied by the high-boost-ratio centrifugal compressor (5) is precooled by the regenerative heat exchanger (6), and the cold source is provided by the cabin exhaust. The gas cooled by the regenerative heat exchanger (6) is further cooled by the secondary heat exchanger (7), and the cold source is provided by the ram air sucked by the fan (14). The gas cooled by the secondary heat exchanger (7) is divided into two paths by the three-way valve (8). One path enters the air separation module (9) of the fuel tank inerting system, and the other path enters the inlet of the hot side channel of the condenser (16) through the hot side channel of the recuperator (15). After being cooled by the cold air at the outlet of the second cooling turbine (16) in the condenser (16), the liquid water is separated by the water separator (18), and the separated liquid water is sprayed at the inlet of the ram air on the cold channel side of the secondary heat exchanger (7). The gas enters the second cooling turbine (16) through the cold side channel of the recuperator (16) to expand and cool down, and then enters the inlet of the cold side channel of the condenser (16). The gas passing through the condenser (16) passes through the self-cleaning primary filter (19), and the gas after primary filtration enters the gas mixing chamber (20).

9. The working method of the energy-saving and clean air-conditioning and fuel tank inerting coupling system based on heat recovery according to claim 6, characterized in that, The specific process of air separation and nitrogen generation and oxygen supply is as follows: The other path of the gas separated by the three-way valve (8) enters the air separation module (9) of the fuel tank inerting system. The gas is separated into oxygen-rich gas and nitrogen-rich gas. The oxygen-rich gas is pressurized by the air centrifugal compressor (13) driven by the output power of the second cooling turbine (16), and then enters the gas mixing chamber (20); the nitrogen-rich gas passes through the control valve (10) and the flame arrester (11) and enters the fuel tank (12) to reduce the oxygen concentration in the gas phase space of the fuel tank and realize the inerting protection of the fuel tank.

10. The working method of the energy-saving and clean environmental control and fuel tank inerting coupling system based on heat recovery according to claim 6, characterized in that, The specific process of clean air filtration is as follows: The oxygen-rich gas pressurized by the air centrifugal compressor (13), the gas initially filtered by the self-cleaning primary air filter (19), and the cabin return air filtered by the self-cleaning medium-efficiency air filtration return device (24) are mixed in the gas mixing chamber (20). The mixed gas is secondarily filtered by the self-cleaning medium-efficiency air filter (21), and finally sent into the cabin (23) through the self-cleaning high-efficiency filter (22). By circulating in this way, the pollution in the clean space of the cabin can be controlled at a relatively stable level within a certain period of time.

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