An aircraft environmental control system for supplying hot water using air circulation

Abstract

The application discloses an aircraft environmental control system for circulating air to supply hot water, so as to reduce energy dissipation. The control system comprises a primary heat exchanger, a compressor, a secondary heat exchanger, a regenerator, a condenser, a water separator, an expander, a first gas-liquid heat exchanger, a second gas-liquid heat exchanger, a hot water tank, a cold water tank and a fan. The primary heat exchanger is connected with the first gas-liquid heat exchanger, the cold water tank is connected with the first gas-liquid heat exchanger, the first gas-liquid heat exchanger is connected with the hot water tank, the hot water tank is connected with the second gas-liquid heat exchanger, the second gas-liquid heat exchanger is connected with the cold water tank and the secondary heat exchanger respectively, the secondary heat exchanger is connected with the primary heat exchanger, the first gas-liquid heat exchanger is connected with the compressor, the compressor is connected with the secondary heat exchanger and the expander respectively, the expander is connected with the regenerator and the condenser respectively, the condenser is connected with the regenerator through the water separator, the regenerator is connected with the secondary heat exchanger, and the fan is opposite to the outlet of the primary heat exchanger.

Description

[0001] Statement: This invention application is a divisional application of Chinese invention patent application filed on September 6, 2021, application number 202111037255.1, entitled "An aircraft environmental control system and method for supplying hot water using air circulation". Technical Field

[0002] This invention relates to the engineering application of air compression and expansion cycles, specifically to an aircraft environmental control system that utilizes air circulation to supply hot water. Background Technology

[0003] With the improvement of people's living standards and the continuous growth of international exchanges, airplanes have become the most popular mode of transportation. To further enhance the comfort of air passengers, airplanes provide hot water services, such as in-flight showers. However, currently, airplanes typically use electric heating to supply hot water, which leads to greater energy consumption as the demand for hot water increases.

[0004] Of all aircraft energy systems, the aircraft environmental control system is responsible for two key functions: (1) providing compressed air to the anti-icing system and passenger air conditioning (PACK), and (2) regulating cabin temperature, pressure (T, P) and humidity. Because components such as primary and secondary heat exchangers consume too much energy in traditional aircraft environmental control systems, the aircraft environmental control system is the largest energy consumer besides the propulsion system.

[0005] The civil aviation industry is increasingly competitive, and the idea is to better utilize the aircraft's own thermal energy cycle to reduce the energy consumption of the aircraft's environmental control system and provide a more energy-efficient hot water supply method. This invention proposes an aircraft environmental control system that utilizes air circulation to supply hot water, thereby optimizing the energy-saving performance of the aircraft's environmental control system and supplying domestic hot water to the aircraft, thus providing a more energy-efficient solution for actual aircraft operation. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide an aircraft environmental control system that uses air circulation to supply hot water, thereby reducing the heat exchange temperature difference of the heat exchanger and thus reducing energy dissipation.

[0007] To address the aforementioned technical problems, the embodiments of the present invention provide the following technical solutions:

[0008] The embodiment of the present application provides an aircraft environmental control system for supplying hot water by air circulation, which comprises a primary heat exchanger, a compressor, a secondary heat exchanger, a regenerator, a condenser, a water separator, an expander, a first gas-liquid heat exchanger, a second gas-liquid heat exchanger, a hot water tank, a cold water tank and a fan; the primary heat exchanger is connected with the first gas-liquid heat exchanger, the cold water tank is connected with the first gas-liquid heat exchanger, the first gas-liquid heat exchanger is connected with the hot water tank, the hot water tank is connected with the second gas-liquid heat exchanger, the second gas-liquid heat exchanger is connected with the cold water tank and the secondary heat exchanger respectively, the secondary heat exchanger is connected with the primary heat exchanger, the first gas-liquid heat exchanger is connected with the compressor, the compressor is connected with the secondary heat exchanger and the expander respectively, the expander is connected with the regenerator and the condenser respectively, the condenser is connected with the regenerator through the water separator, the regenerator is connected with the secondary heat exchanger, and the fan is opposite to the outlet of the primary heat exchanger.

[0009] Preferably, the fan, the expander and the compressor are coaxially arranged.

[0010] Preferably, the primary heat exchanger, the secondary heat exchanger, the regenerator, the condenser, the first gas-liquid heat exchanger and the second gas-liquid heat exchanger are heat exchange units.

[0011] Preferably, the primary heat exchanger comprises a first hot side bleed air input end, a first hot side bleed air output end, a first cold side ram air input end, and a first cold side ram air output end; the secondary heat exchanger comprises a second hot side bleed air input end, a second hot side bleed air output end, a second cold side ram air input end, and a second cold side ram air output end; the regenerator comprises a third hot side bleed air input end, a third hot side bleed air output end, a first cold side bleed air input end, and a first cold side bleed air output end; the condenser comprises a fourth hot side bleed air input end, a fourth hot side bleed air output end, a second cold side bleed air input end, and a second cold side bleed air output end; the first gas-liquid heat exchanger comprises a fifth hot side bleed air input end, a fifth hot side bleed air output end, a cold side cold source input end, and a cold side cold source output end; the second gas-liquid heat exchanger comprises a hot side heat source input end, a hot side heat source output end, a third cold side ram air input end, and a third cold side ram air output end; the first hot side bleed air input end is in communication with the outside, the first hot side bleed air output end is connected with the fifth hot side bleed air input end, the fifth hot side bleed air output end is connected with the compressor working medium input end of the compressor, the compressor working medium output end of the compressor is connected with the second hot side bleed air input end, the second hot side bleed air output end is connected with the third hot side bleed air input end, the third hot side bleed air output end is connected with the fourth hot side bleed air input end, the fourth hot side bleed air output end is connected with the water separator working medium input end of the water separator, the water separator working medium output end of the water separator is connected with the first cold side bleed air input end, the first cold side bleed air output end is connected with the expander working medium input end of the expander, the expander working medium output end of the expander is connected with the second cold side bleed air input end, and the second cold side bleed air output end is in communication with the outside; the cold water tank working medium output end of the cold water tank is connected with the cold side cold source input end, the cold side cold source output end is connected with the hot water tank working medium input end of the hot water tank, the hot water tank working medium output end of the hot water tank is connected with the hot side heat source input end, and the hot side heat source output end is connected with the cold water tank working medium input end of the cold water tank; the compressor is driven to operate by the expansion work output by the expander.

[0012] Compared with the prior art, the aircraft environmental control system for supplying hot water by air circulation of the embodiment of the application can reduce the heat exchange temperature difference of the heat exchanger, thereby reducing energy dissipation. The application reduces the heat exchange temperature difference of the primary heat exchanger and the secondary heat exchanger of the aircraft environmental control system, thereby reducing energy dissipation generated by heat exchange, and further reducing system energy consumption. The application also meets the refrigeration capacity supplied by the traditional aircraft environmental control system. In the application, high-temperature bleed air flows out of the system into the cabin in the form of low-temperature bleed air after heat exchange through the aircraft environmental control system, thereby realizing the refrigeration capacity supplied by the aircraft environmental control system. Meanwhile, the application can also supply hot water for life on the aircraft, reducing the demand for electricity on the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 is a structural diagram of the embodiment of the application.

[0014] The components include: primary heat exchanger 1, first hot-side bleed air inlet 1a, first hot-side bleed air outlet 1b, first cold-side ram air inlet 1c, first cold-side ram air outlet 1d; compressor 2, compressor working fluid inlet 2a, compressor working fluid outlet 2b; secondary heat exchanger 3, second hot-side bleed air inlet 3a, second hot-side bleed air outlet 3b, second cold-side ram air inlet 3c, second cold-side ram air outlet 3d; regenerator 4, third hot-side bleed air inlet 4a, third hot-side bleed air outlet 4b, first cold-side bleed air inlet 4c, first cold-side bleed air outlet 4d; condenser 5, fourth hot-side bleed air inlet 5a, fourth hot-side bleed air outlet 5b, second cold-side bleed air inlet 5c; and so on. Second cold-side bleed air output terminal 5d, water separator 6, water separator working fluid input terminal 6a, water separator bleed air output terminal 6b, expander 7, expander working fluid input terminal 7a, expander working fluid output terminal 7b, first gas-liquid heat exchanger 8, fifth hot-side bleed air input terminal 8a, fifth hot-side bleed air output terminal 8b, cold-side cold source input terminal 8c, cold-side cold source output terminal 8d, second gas-liquid heat exchanger 9, hot-side heat source input terminal 9a, hot-side heat source output terminal 9b, third cold-side ram air input terminal 9c, third cold-side ram air output terminal 9d, hot water tank 10, hot water tank working fluid input terminal 10a, hot water tank working fluid output terminal 10b, cold water tank 11, cold water tank working fluid input terminal 11a, cold water tank working fluid output terminal 11b, fan 12. Detailed Implementation

[0015] The technical solution of the present invention will now be described in detail with reference to the accompanying drawings.

[0016] like Figure 1 As shown, the aircraft environmental control system for supplying hot water using air circulation according to an embodiment of the present invention includes a primary heat exchanger 1, a compressor 2, a secondary heat exchanger 3, a regenerator 4, a condenser 5, a water separator 6, an expander 7, a first gas-liquid heat exchanger 8, a second gas-liquid heat exchanger 9, a hot water tank 10, a cold water tank 11, and a fan 12. The primary heat exchanger 1 is connected to the first gas-liquid heat exchanger 8, the cold water tank 11 is connected to the first gas-liquid heat exchanger 8, the first gas-liquid heat exchanger 8 is connected to the hot water tank 10, the hot water tank 10 is connected to the second gas-liquid heat exchanger 9, the second gas-liquid heat exchanger 9 is connected to the cold water tank 11 and the secondary heat exchanger 3 respectively, the secondary heat exchanger 3 is connected to the primary heat exchanger 1, the first gas-liquid heat exchanger 8 is connected to the compressor 2, the compressor 2 is connected to the secondary heat exchanger 3 and the expander 7 respectively, the expander 7 is connected to the regenerator 4 and the condenser 5 respectively, the condenser 5 is connected to the regenerator 4 through the water separator 6, the regenerator 4 is connected to the secondary heat exchanger 3, and the fan 12 is opposite to the outlet of the primary heat exchanger 1.

[0017] The control system of the above embodiment comprises an aircraft environmental control system and a hot water supply cycle, wherein the aircraft environmental control system comprises a primary heat exchanger 1, a compressor 2, a secondary heat exchanger 3, a regenerator 4, an expander 7, a condenser 5, a water separator 6 and a fan 12. The hot water supply cycle comprises a first gas-liquid heat exchanger 8, a second gas-liquid heat exchanger 9, a hot water tank 10 and a cold water tank 11.

[0018] Preferably, the fan 12, the expander 7 and the compressor 2 are coaxially arranged. Of course, other mechanical transmission devices can also be used to connect the fan 12, the expander 7 and the compressor 2. The expander 7 transmits expansion work to the compressor 2 and the fan 12.

[0019] Preferably, the primary heat exchanger 1, the secondary heat exchanger 3, the regenerator 4, the condenser 5, the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9 are heat exchange units. The primary heat exchanger 1, the secondary heat exchanger 3, the regenerator 4 and the condenser 5 are all heat exchangers between gases. In the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9, heat exchange is between a gas and a liquid.

[0020] Preferably, the primary heat exchanger 1 comprises a first hot side bleed air input end 1a, a first hot side bleed air output end 1b, a first cold side ram air input end 1c and a first cold side ram air output end 1d. The secondary heat exchanger 3 comprises a second hot side bleed air input end 3a, a second hot side bleed air output end 3b, a second cold side ram air input end 3c and a second cold side ram air output end 3d. The regenerator 4 comprises a third hot side bleed air input end 4a, a third hot side bleed air output end 4b, a first cold side bleed air input end 4c and a first cold side bleed air output end 4d. The condenser 5 comprises a fourth hot side bleed air input end 5a, a fourth hot side bleed air output end 5b, a second cold side bleed air input end 5c and a second cold side bleed air output end 5d. The first gas-liquid heat exchanger 8 comprises a fifth hot side bleed air input end 8a, a fifth hot side bleed air output end 8b, a cold side cold source input end 8c and a cold side cold source output end 8d. The second gas-liquid heat exchanger 9 comprises a hot side heat source input end 9a, a hot side heat source output end 9b, a third cold side ram air input end 9c and a third cold side ram air output end 9d. The first hot side bleed air input end 1a is connected with the outside, the first hot side bleed air output end 1b is connected with the fifth hot side bleed air input end 8a, the fifth hot side bleed air output end 8b is connected with the compressor working medium input end 2a of the compressor 2, the compressor working medium output end 2b of the compressor 2 is connected with the second hot side bleed air input end 3a, the second hot side bleed air output end 3b is connected with the third hot side bleed air input end 4a, the third hot side bleed air output end 4b is connected with the fourth hot side bleed air input end 5a, the fourth hot side bleed air output end 5b is connected with the water separator working medium input end 6a of the water separator 6, the water separator working medium output end 6b of the water separator 6 is connected with the first cold side bleed air input end 4c, the first cold side bleed air output end 4d is connected with the expander working medium input end 7a of the expander 7, the expander working medium output end 7b of the expander 7 is connected with the second cold side bleed air input end 5c, the second cold side bleed air output end 5d is connected with the outside; the cold water tank working medium output end 11b of the cold water tank 11 is connected with the cold side cold source input end 8c, the cold side cold source output end 8d is connected with the hot water tank working medium input end 10a of the hot water tank 10, the hot water tank working medium output end 10b of the hot water tank 10 is connected with the hot side heat source input end 9a, the hot side heat source output end 9b is connected with the cold water tank working medium input end 11a of the cold water tank 11; the compressor 2 is driven to operate by the expansion work outputted by the expander 7.

[0021] The first hot side bleed air input end 1a is connected with the engine, and the high-temperature bleed air generated by the aircraft engine is introduced into the hot side of the primary heat exchanger 1. The third cold side ram air input end 9c of the second gas-liquid heat exchanger 9 is connected with the outside, and the ram air outside the cabin is introduced into the cold side of the second gas-liquid heat exchanger 9.

[0022] The control method of the above-mentioned control system comprises three processes.

[0023] The first process is as follows: Aircraft engine bleed air enters the control system through the first hot-side bleed air inlet 1a of the primary heat exchanger 1. The bleed air exchanges heat with the ram air on the cold side of the primary heat exchanger 1. Subsequently, the bleed air exchanges heat with the chilled water in the first gas-liquid heat exchanger 8. After being pressurized by the compressor 2, it is discharged and flows into the hot side of the secondary heat exchanger 3 to exchange heat with the ram air. Then, the cooled bleed air flows sequentially into the hot sides of the regenerator 4 and condenser 5 for further cooling. After recooling, the bleed air is first separated from the water by the water separator 6, and the dried bleed air returns to the cold side of the regenerator 4 for reheating. Then, it flows into the expander 7 for expansion and further cooling. Next, the bleed air flows into the cold side of the condenser 5 for reheating, and finally flows into the aircraft's mixing chamber through the second cold-side bleed air outlet 5d. The air flowing out from the second cold-side bleed air outlet 5d is the chilled air supplied to the aircraft cabin.

[0024] The second process is as follows: The low-temperature, low-pressure ram air from outside the aircraft cabin first flows into the cold side of the second gas-liquid heat exchanger 9, is preheated by hot water, and then flows out of the second gas-liquid heat exchanger 9. Then, the ram air enters the secondary heat exchanger 3 and exchanges heat with the high-temperature bleed air on the hot side of the secondary heat exchanger 3. After that, it flows into the primary heat exchanger 1 for heat exchange. Finally, the ram air is discharged outside the cabin by the fan 12.

[0025] The third process is as follows: the cold water in the cold water tank 11 enters the cold side of the first gas-liquid heat exchanger 8. After exchanging heat with the induced air on the hot side of the first gas-liquid heat exchanger 8, the cold water is heated to the set hot water temperature and flows into the hot water tank 10. The hot water flows out of the hot water tank 10 and enters the hot side of the second gas-liquid heat exchanger 9. After exchanging heat with the external ram air entering the system on the cold side of the second gas-liquid heat exchanger 9, the water is cooled to the cold water tank temperature and flows back into the cold water tank 11.

[0026] In the first process, the induced air serves as a heat source and exchanges heat with the cold water on the cold side of the first gas-liquid heat exchanger 8, raising the temperature of the cold water to hot water.

[0027] The control methods include a self-circulation mode and a hot water supply mode.

[0028] In the self-circulation mode, the water flow rate in the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9 is controlled to be the same. After the cold water in the first gas-liquid heat exchanger 8 is heated to hot water by the high-temperature induced air, it flows into the second gas-liquid heat exchanger 9 through the hot water tank 10. After preheating the ram air, the water temperature drops to the same temperature as the water in the cold water tank 11, and then returns to the cold water tank 11 to form a cycle.

[0029] In the self-circulation mode, the cold water from the cold water tank 11 enters the first gas-liquid heat exchanger 8, is heated by the high-temperature bleed air, and then enters the hot water tank 10 at a constant flow rate. The hot water then flows into the second gas-liquid heat exchanger 9 from the hot water tank 10 at the same flow rate, exchanges heat with the low-temperature ram air in the second gas-liquid heat exchanger 9, and then returns to the cold water tank 11 after the water temperature is restored to the same temperature as the cold water in the cold water tank 11, thereby forming a self-circulation mode. In the self-circulation mode, the hot water circulation can reduce the inlet temperature of the compressor 2, thereby improving the working condition of the compressor 2 and reducing the energy consumption. The self-circulation mode can also reduce the heat exchange temperature difference of the primary heat exchanger 1 and the secondary heat exchanger 3, thereby reducing the energy dissipation during heat exchange.

[0030] In the hot water supply mode, the water flow rates in the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9 are controlled to be different, reducing the water flow from the first gas-liquid heat exchanger 8 into the second gas-liquid heat exchanger 9. The water that does not enter the second gas-liquid heat exchanger 9 is stored in the hot water tank 10 in the form of hot water to provide hot water for the aircraft.

[0031] In the hot water supply mode, the same working principle as in the self-circulation mode is used. However, the difference is that by adjusting the water flow rate of the hot water tank 10 into the second gas-liquid heat exchanger 9, the amount of hot water participating in the aircraft environmental control system is reduced, and the hot water is stored in the hot water tank 10 in the form of domestic hot water.

[0032] The hot water supply mode can reduce the inlet temperature of the compressor 2, thereby improving the working condition of the compressor 2 and reducing the energy consumption. The self-circulation mode can also reduce the heat exchange temperature difference of the primary heat exchanger 1 and the secondary heat exchanger 3, thereby reducing the energy dissipation during heat exchange. By simply adjusting the water flow rates of the two gas-liquid heat exchangers, the amount of hot water participating in the hot water circulation is reduced, and the hot water is stored in the hot water tank 10 in the form of domestic hot water, thereby providing hot water for aircraft users. Therefore, the present application can obtain hot water for aircraft by controlling the water flow rate in a more simple, flexible, and adjustable manner.

[0033] The embodiment of the present application improves the problem of excessive energy consumption caused by the aircraft environmental control system and the aircraft hot water supply mode. After adding the hot water circulation in the system of the embodiment, the circulating hot water preheats the ram air, reduces the heat exchange temperature difference of the primary heat exchanger 1 and the secondary heat exchanger 3, and thereby reduces the heat exchange energy consumption. In addition, the addition of the hot water circulation reduces the suction inlet temperature of the compressor 2, improves the working condition of the compressor 2, and thereby reduces the energy consumption of the compressor 2. By establishing the connection between the components of the aircraft environmental control system and utilizing the saved heat to heat water for the aircraft, the present application utilizes the energy dissipated due to the excessive heat exchange temperature difference of the primary heat exchanger and the secondary heat exchanger to heat water.

[0034] The high-temperature and high-pressure bleed air is used as a heat source of the aircraft environmental control system. The high-temperature and high-pressure bleed air generated by the engine enters the system from the primary heat exchanger 1 hot side, is heat-exchanged through the primary heat exchanger 1, and then enters the first gas-liquid heat exchanger 8 for temperature reduction again. The bleed air after temperature reduction is pressurized and heated in the compressor 2, and then flows into the secondary heat exchanger 3 for temperature reduction. The bleed air flows into the regenerator 4 hot side for heat exchange, and then enters the condenser 5 for condensation. Subsequently, the bleed air enters the water separator 6 for water separation. The dry bleed air flows out of the water separator 6, enters the regenerator 4 cold side for temperature increase, and then flows into the expander 7 for work expansion. The temperature of the bleed air is reduced, and finally the bleed air flows into the condenser 5 cold side for temperature increase to meet the cooling demand of the passenger cabin and enters the aircraft mixing chamber.

[0035] The low-temperature ram air outside the cabin is used as a cold source of the aircraft environmental control system. The ram air enters the system from the second gas-liquid heat exchanger 9 cold side, is heat-exchanged with the hot water in the second gas-liquid heat exchanger 9, and then enters the secondary heat exchanger 3 cold side for heat exchange. The ram air takes away the heat of the bleed air on the secondary heat exchanger 3 hot side, and then enters the primary heat exchanger 1 cold side for heat exchange with the high-temperature bleed air. The ram air is discharged outside the cabin by the fan 12. There are three working media in the system of the application, i.e., the ram air outside the cabin, the high-temperature bleed air and water. Through the circulation of the three working media, the hot water supply on the aircraft and the cold air supply in the passenger cabin are realized.

[0036] In the self-circulation mode of the system, the first gas-liquid heat exchanger 8 cold side and the second gas-liquid heat exchanger 9 hot side are connected in series. The cold water in the cold water tank 11 is pumped into the first gas-liquid heat exchanger 8 cold side. The cold water is heat-exchanged with the bleed air on the first gas-liquid heat exchanger 8 hot side, and then flows into the second gas-liquid heat exchanger 9 hot side to preheat the ram air. Thus, the hot water is cooled to the water temperature in the cold water tank 11, and then flows into the cold water tank 11.

[0037] In the hot water supply mode of the system, the first gas-liquid heat exchanger 8 cold side and the second gas-liquid heat exchanger 9 hot side are connected in series. The cold water in the cold water tank 11 is pumped into the first gas-liquid heat exchanger 8 cold side. The cold water is heat-exchanged with the bleed air on the first gas-liquid heat exchanger 8 hot side, and then flows into the second gas-liquid heat exchanger 9 hot side to preheat the ram air. Thus, the hot water is cooled to the water temperature in the cold water tank 11, and then flows into the cold water tank 11.

[0038] The water flow circulation formed among the cold water tank 11, the hot water tank 10, the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9 in the application reduces the heat exchange temperature difference of the primary heat exchanger 1 and the secondary heat exchanger 3, thereby improving the energy saving of the aircraft environmental control system and supplying hot water for the aircraft. The system in the application contains a hot water circulation system, the cabin outside ram air entering the system is preheated by the hot water in the circulation, and the high temperature bleed air discharged from the hot side of the primary heat exchanger is cooled by the cold water in the circulation. In this way, the heat exchange temperature difference of the primary heat exchanger and the secondary heat exchanger is reduced, the energy dissipation is reduced, the compressor inlet suction temperature is reduced, the operation condition of the compressor is improved, and the operation energy consumption is reduced. The hot water circulation in the system of the application can also be simply and conveniently adjusted, the hot water in the hot water tank is reduced, and the hot water is stored in the form of domestic hot water.

Claims

1. An aircraft environmental control system for supplying hot water using air circulation, characterized by, The system comprises a primary heat exchanger (1), a compressor (2), a secondary heat exchanger (3), a regenerator (4), a condenser (5), a water separator (6), an expander (7), a first gas-liquid heat exchanger (8), a second gas-liquid heat exchanger (9), a hot water tank (10), a cold water tank (11), and a fan (12); The primary heat exchanger (1) is connected with the first gas-liquid heat exchanger (8), the cold water tank (11) is connected with the first gas-liquid heat exchanger (8), the first gas-liquid heat exchanger (8) is connected with the hot water tank (10), the hot water tank (10) is connected with the second gas-liquid heat exchanger (9), the second gas-liquid heat exchanger (9) is connected with the cold water tank (11) and the secondary heat exchanger (3) respectively, the secondary heat exchanger (3) is connected with the primary heat exchanger (1), the first gas-liquid heat exchanger (8) is connected with the compressor (2), the compressor (2) is connected with the secondary heat exchanger (3) and the expander (7) respectively, the expander (7) is connected with the regenerator (4) and the condenser (5) respectively, the condenser (5) is connected with the water separator (6) and the regenerator (4), the regenerator (4) is connected with the secondary heat exchanger (3), and the fan (12) is opposite to the outlet of the primary heat exchanger (1); The system has a self-circulation mode and a hot water supply mode: In the self-circulation mode, the water flow in the first gas-liquid heat exchanger (8) and the second gas-liquid heat exchanger (9) is controlled to be the same, the cold water in the first gas-liquid heat exchanger (8) is heated to hot water by high-temperature bleed air, then flows into the second gas-liquid heat exchanger (9) to preheat the ram air, and then the water temperature is reduced to the same temperature in the cold water tank (11), and then returns to the cold water tank (11) to form a cycle; In the hot water supply mode, the water flow speed in the first gas-liquid heat exchanger (8) and the second gas-liquid heat exchanger (9) is controlled to be different, the water flow in the first gas-liquid heat exchanger (8) is reduced to flow into the second gas-liquid heat exchanger (9), the water that does not enter the second gas-liquid heat exchanger (9) is stored in the hot water tank (10) in the form of hot water to supply hot water for the aircraft.

2. An aircraft environmental control system for supplying hot water using air circulation as claimed in claim 1, characterized in that The fan (12), the expander (7) and the compressor (2) are coaxially arranged.

3. An aircraft environmental control system for supplying hot water using air circulation as defined in claim 1, characterized in that The primary heat exchanger (1), the secondary heat exchanger (3), the regenerator (4), the condenser (5), the first gas-liquid heat exchanger (8) and the second gas-liquid heat exchanger (9) are heat exchange units.

4. The aircraft for supplying hot water by air circulation according to claim 1 An environmental control system characterized by The primary heat exchanger (1) comprises a first hot side bleed air input end (1a), a first hot side bleed air output end (1b), a first cold side ram air input end (1c) and a first cold side ram air output end (1d); The secondary heat exchanger (3) comprises a second hot side bleed air input end (3a), a second hot side bleed air output end (3b), a second cold side ram air input end (3c) and a second cold side ram air output end (3d); The regenerator (4) comprises a third hot side bleed air input end (4a), a third hot side bleed air output end (4b), a first cold side bleed air input end (4c) and a first cold side bleed air output end (4d); The condenser (5) comprises a fourth hot-side bleed air input end (5a), a fourth hot-side bleed air output end (5b), a second cold-side bleed air input end (5c), and a second cold-side bleed air output end (5d); The first gas-liquid heat exchanger (8) comprises a fifth hot-side bleed air input end (8a), a fifth hot-side bleed air output end (8b), a cold-side cold source input end (8c), and a cold-side cold source output end (8d); The second gas-liquid heat exchanger (9) comprises a hot-side heat source input end (9a), a hot-side heat source output end (9b), a third cold-side bleed air input end (9c), and a third cold-side bleed air output end (9d); The first hot-side bleed air input end (1a) is connected with the outside, the first hot-side bleed air output end (1b) is connected with the fifth hot-side bleed air input end (8a), the fifth hot-side bleed air output end (8b) is connected with the compressor working medium input end (2a) of the compressor (2), the compressor working medium output end (2b) of the compressor (2) is connected with the second hot-side bleed air input end (3a), the second hot-side bleed air output end (3b) is connected with the third hot-side bleed air input end (4a), the third hot-side bleed air output end (4b) is connected with the fourth hot-side bleed air input end (5a), the fourth hot-side bleed air output end (5b) is connected with the water separator working medium input end (6a) of the water separator (6), the water separator working medium output end (6b) of the water separator (6) is connected with the first cold-side bleed air input end (4c), the first cold-side bleed air output end (4d) is connected with the expander working medium input end (7a) of the expander (7), the expander working medium output end (7b) of the expander (7) is connected with the second cold-side bleed air input end (5c), the second cold-side bleed air output end (5d) is connected with the outside, the cold-water tank working medium output end (11b) of the cold-water tank (11) is connected with the cold-side cold source input end (8c), the cold-side cold source output end (8d) is connected with the hot-water tank working medium input end (10a) of the hot-water tank (10), the hot-water tank working medium output end (10b) of the hot-water tank (10) is connected with the hot-side heat source input end (9a), and the hot-side heat source output end (9b) is connected with the cold-water tank working medium input end (11a) of the cold-water tank (11); the compressor (2) is driven to operate by the expansion work output by the expander (7).

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