阅读说明：本技术 一种利用空气循环供应热水的飞机环境控制系统及方法 (Airplane environment control system and method for supplying hot water by air circulation ) 是由 程清 上官震 王涵 于 2021-09-06 设计创作，主要内容包括：本发明公开了一种利用空气循环供应热水的飞机环境控制系统及方法,以减轻能量耗散。控制系统包括初级换热器、压缩机、次级换热器、回热器、冷凝器、水分离器、膨胀机、第一气液换热器、第二气液换热器、热水箱、冷水箱和风扇；初级换热器和第一气液换热器连接,冷水箱和第一气液换热器连接,第一气液换热器和热水箱连接,热水箱和第二气液换热器连接,第二气液换热器分别与冷水箱和次级换热器连接,次级换热器和初级换热器连接,第一气液换热器和压缩机连接,压缩机分别与次级换热器和膨胀机连接,膨胀机分别与回热器和冷凝器连接,冷凝器通过水分离器和回热器连接,回热器和次级换热器连接,风扇和初级换热器的出口相对。(The invention discloses an aircraft environment control system and method for supplying hot water by air circulation, which aims to reduce energy dissipation. The control system comprises a primary heat exchanger, a compressor, a secondary heat exchanger, a heat 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 respectively connected with the cold water tank and the secondary heat exchanger, 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 respectively connected with the secondary heat exchanger and the expander, the expander is respectively connected with the heat regenerator and the condenser, the condenser is connected with the heat regenerator through the water separator, the heat regenerator is connected with the secondary heat exchanger, and the outlet of the fan is opposite to the outlet of the primary heat exchanger.)

1. An aircraft environment control system for supplying hot water by air circulation is characterized by comprising a primary heat exchanger (1), a compressor (2), a secondary heat exchanger (3), a heat 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 respectively connected with the cold water tank (11) and the secondary heat exchanger (3), 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 respectively connected with the secondary heat exchanger (3) and the expander (7), the expander (7) is respectively connected with the heat regenerator (4) and the condenser (5), the condenser (5) is connected with the heat regenerator (4) through the water separator (6), the heat regenerator (4) is connected with the secondary heat exchanger (3), and the outlet of the fan (12) is opposite to the primary heat exchanger (1).

2. An aircraft environmental control system for supplying hot water by means of air circulation according to claim 1, characterized in that said fan (12), expander (7) and compressor (2) are arranged coaxially.

3. An aircraft environmental control system for supplying hot water by means of air circulation according to 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 all heat exchange units.

4. An aircraft environmental control system for supplying hot water with air circulation according to claim 1, characterized in that the primary heat exchanger (1) comprises a first hot-side bleed air input (1a), a first hot-side bleed air output (1b), a first cold-side ram air input (1c), a first cold-side ram air output (1 d);

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 (3 d);

the heat 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 (4 d);

the condenser (5) comprises a fourth hot-side air-entraining input end (5a), a fourth hot-side air-entraining output end (5b), a second cold-side air-entraining input end (5c) and a second cold-side air-entraining output end (5 d);

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 (8 d);

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 (9 d);

the first hot side air-entraining input end (1a) is communicated with the outside, the first hot side air-entraining output end (1b) is connected with the fifth hot side air-entraining input end (8a), the fifth hot side air-entraining 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 air-entraining input end (3a), the second hot side air-entraining output end (3b) is connected with the third hot side air-entraining input end (4a), the third hot side air-entraining output end (4b) is connected with the fourth hot side air-entraining input end (5a), the fourth hot side air-entraining 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 air-entraining input end (4c), the first cold side air-entraining output end (4d) is connected with an expander working medium input end (7a) of the expander (7), an expander working medium output end (7b) of the expander (7) is connected with the second cold side air-entraining input end (5c), and the second cold side air-entraining output end (5d) is communicated with the outside; a cold water tank working medium output end (11b) of the cold water tank (11) is connected with a cold side cold source input end (8c), a cold side cold source output end (8d) is connected with a hot water tank working medium input end (10a) of the hot water tank (10), a hot water tank working medium output end (10b) of the hot water tank (10) is connected with a hot side heat source input end (9a), and a 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).

5. A method of controlling an aircraft environmental control system for supplying hot water using air circulation according to any one of claims 1 to 4, the method comprising:

leading air of an aircraft engine to enter a control system through a first hot side air-leading input end (1a) of a primary heat exchanger (1), carrying out heat exchange on the air-leading and ram air on the cold side of the primary heat exchanger (1), then carrying out heat exchange on the air-leading and cold water in a first air-liquid heat exchanger (8), pressurizing by a compressor (2), discharging, and flowing into the hot side of a secondary heat exchanger (3) to carry out heat exchange with the ram air; then, the cooled bleed air sequentially flows into the heat regenerator (4) and the hot side of the condenser (5) for recooling; the moisture in the bleed air after re-cooling is separated by a water separator (6), the dried bleed air returns to the cold side of a heat regenerator (4) for reheating, then flows into an expander (7) for expansion work and further cooling, then flows into the cold side of a condenser (5) for reheating, and finally flows into a mixing chamber of an airplane through a second cold-side bleed air output end (5 d);

firstly, low-temperature and low-pressure ram air outside the cabin of the airplane flows into a cold side of a second gas-liquid heat exchanger (9), flows out of the second gas-liquid heat exchanger (9) after being preheated by hot water, then enters a secondary heat exchanger (3), exchanges heat with high-temperature bleed air at the hot side of the secondary heat exchanger (3), flows into a primary heat exchanger (1), exchanges heat, and finally is discharged outside the cabin by a fan (12);

cold water in the cold water tank (11) enters the cold side of the first gas-liquid heat exchanger (8), after heat exchange is carried out on the cold water and bleed air at the hot side of the first gas-liquid heat exchanger (8), the temperature is raised to a set hot water temperature, the cold water flows into the hot water tank (10), hot water flows out of the hot water tank (10), enters the hot side of the second gas-liquid heat exchanger (9), exchanges heat with outside-cabin ram air entering the system at the cold side of the second gas-liquid heat exchanger (9), is cooled to the temperature of the cold water tank, and flows back to the cold water tank (11).

6. The control method according to claim 5, characterized by comprising a self-circulation mode, wherein the water flow in the first gas-liquid heat exchanger (8) and the water flow in the second gas-liquid heat exchanger (9) are controlled to be the same, cold water in the first gas-liquid heat exchanger (8) flows into the second gas-liquid heat exchanger (9) after being heated to hot water by high-temperature bleed air, passes through the hot water tank (10), and after the flushing air is preheated, the water temperature is reduced to the same water temperature in the cold water tank (11), and then returns to the cold water tank (11), so that circulation is formed.

7. The control method according to claim 5, characterized by further comprising a hot water supply mode, wherein the flow rates of water in the first gas-liquid heat exchanger (8) and the second gas-liquid heat exchanger (9) are controlled to be different, water in the first gas-liquid heat exchanger (8) is reduced to flow into the second gas-liquid heat exchanger (9), water which does not enter the second gas-liquid heat exchanger (9) is stored in a hot water tank (10) in the form of hot water, and hot water is supplied to the airplane.

Technical Field

The invention belongs to the application of an engineering technology of air compression expansion circulation, and particularly relates to an aircraft environment control system and method for supplying hot water by air circulation.

Background

With the improvement of the quality of life of people and the continuous increase of international communication, airplanes have become the most popular vehicles. To further enhance the comfort of aircraft passenger trips, aircraft have provided hot water service to passengers, such as an aerial shower. However, aircraft are currently typically supplied with hot water by electrical heating, which results in greater aircraft energy consumption as aircraft hot water demand increases.

Among 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 the Passenger Air Conditioners (PACK), and (2) regulating cabin temperature, pressure (T, P), and humidity. Because the energy consumption of components such as the primary heat exchanger and the secondary heat exchanger is too large in the conventional aircraft environment control system, the aircraft environment control system is the largest energy consumer except for the propulsion power system.

Now, the competition of the civil aviation industry is more severe, and how to better utilize the self heat energy circulation of the airplane to achieve the purposes of reducing the energy consumption of an airplane environment control system and providing a more energy-saving hot water supply mode is assumed. The invention provides an aircraft environment control system for supplying hot water by air circulation, which is used for optimizing the energy-saving performance of the aircraft environment control system and supplying domestic hot water to an aircraft, thereby providing a more energy-saving scheme for the actual operation of the aircraft.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the aircraft environment control system and method for supplying hot water by air circulation are provided, and the heat exchange temperature difference of a heat exchanger is reduced, so that energy dissipation is reduced.

In order to solve the above technical problems, embodiments of the present invention provide the following technical solutions:

in a first aspect, an embodiment of the present invention provides an aircraft environmental control system for supplying hot water by air circulation, including a primary heat exchanger, a compressor, a secondary heat exchanger, a heat 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 respectively connected with the cold water tank and the secondary heat exchanger, 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 respectively connected with the secondary heat exchanger and the expander, the expander is respectively connected with the heat regenerator and the condenser, the condenser is connected with the heat regenerator through the water separator, the heat regenerator is connected with the secondary heat exchanger, and the outlet of the fan is opposite to the outlet of the primary heat exchanger.

Preferably, the fan, the expander and the compressor are coaxially arranged.

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

Preferably, the primary heat exchanger comprises a first hot side bleed air input, a first hot side bleed air output, a first cold side ram air input, a first cold side ram air output; the secondary heat exchanger comprises a second hot side air-entraining input end, a second hot side air-entraining output end, a second cold side ram air input end and a second cold side ram air output end; the heat regenerator comprises a third hot side air-entraining input end, a third hot side air-entraining output end, a first cold side air-entraining input end and a first cold side air-entraining output end; the condenser comprises a fourth hot side air-entraining input end, a fourth hot side air-entraining output end, a second cold side air-entraining input end and a second cold side air-entraining 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 air-entraining input end is communicated with the outside, the first hot side air-entraining output end is connected with the fifth hot side air-entraining input end, the fifth hot side air-entraining output end is connected with a compressor working medium input end of the compressor, a compressor working medium output end of the compressor is connected with the second hot side air-entraining input end, the second hot side air-entraining output end is connected with the third hot side air-entraining input end, the third hot side air-entraining output end is connected with the fourth hot side air-entraining input end, the fourth air-entraining output end is connected with a water separator working medium input end of a water separator, a water separator working medium output end of the water separator is connected with the first cold side air-entraining input end, the first cold side air-entraining output end is connected with an expander working medium input end of the expander, the expander working medium output end of the expander is connected with the second cold side air-entraining input end of the expander, and the second cold side air-entraining output end is communicated 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 by the expansion work output by the expander to operate.

In a second aspect, embodiments of the present invention further provide a method for controlling an aircraft environmental control system that supplies hot water using air circulation, the method including: the method comprises the following steps that bleed air of an aircraft engine enters a control system through a first hot side bleed air input end of a primary heat exchanger, the bleed air exchanges heat with ram air on a cold side of the primary heat exchanger, then the bleed air exchanges heat with cold water in a first gas-liquid heat exchanger, the bleed air is discharged after being pressurized by a compressor, and the bleed air flows into a hot side of a secondary heat exchanger to exchange heat with the ram air; then, the cooled bleed air flows into the heat regenerator and the hot side of the condenser in sequence for recooling; the moisture in the cooled bleed air is separated by the water separator, the dried bleed air returns to the cold side of the heat regenerator for reheating, then flows into the expander for expansion work and further cooling, then flows into the cold side of the condenser for reheating, and finally flows into a mixing chamber of the airplane through a second cold-side bleed air output end; firstly, low-temperature and low-pressure ram air outside the airplane cabin flows into a cold side of a second gas-liquid heat exchanger, flows out of the second gas-liquid heat exchanger after being preheated by hot water, then enters a secondary heat exchanger, exchanges heat with high-temperature bleed air at the hot side of the secondary heat exchanger, flows into a primary heat exchanger for heat exchange, and finally is discharged out of the airplane cabin through a fan; and after heat exchange is carried out between the cold water and bleed air at the hot side of the first gas-liquid heat exchanger, the cold water is heated to a set hot water temperature and flows into the hot water tank, and hot water flows out of the hot water tank, enters the hot side of the second gas-liquid heat exchanger, exchanges heat with cabin outside ram air at the cold side of the second gas-liquid heat exchanger, is cooled to the water temperature of the cold water tank, and flows back to the cold water tank.

Preferably, the control method includes a self-circulation mode, in the self-circulation mode, the water flow rates in the first gas-liquid heat exchanger and the second gas-liquid heat exchanger are controlled to be the same, cold water in the first gas-liquid heat exchanger is heated to hot water by high-temperature bleed air, then flows into the second gas-liquid heat exchanger through the hot water tank, and after the flushing air is preheated, the water temperature is reduced to the same water temperature in the cold water tank, and then returns to the cold water tank to form circulation.

Preferably, the control method further includes a hot water supply mode, the flow rates of the water in the first gas-liquid heat exchanger and the second gas-liquid heat exchanger are controlled to be different, the water in the first gas-liquid heat exchanger is reduced to flow into the second gas-liquid heat exchanger, the water which does not flow into the second gas-liquid heat exchanger is stored in the hot water tank in the form of hot water, and hot water is supplied to the aircraft.

Compared with the prior art, the aircraft environment control system and method for supplying hot water by air circulation can reduce the heat exchange temperature difference of the heat exchanger, thereby reducing energy dissipation. The invention reduces the heat exchange temperature difference of the primary heat exchanger and the secondary heat exchanger of the aircraft environment control system, thereby reducing the energy dissipation generated by heat exchange and further reducing the energy consumption of the system. The present invention also satisfies the refrigeration capacity supplied by conventional aircraft environmental control systems. In this application, high temperature bleed air finally gets into the passenger cabin with low temperature bleed air form outflow system after through environmental control system's heat transfer to realize the refrigerating output that aircraft environmental control system supplied. Simultaneously, this application can also provide life hot water for the aircraft, reduces the demand of the last power consumption of aircraft.

Drawings

FIG. 1 is a block diagram of an embodiment of the present invention.

Wherein, the primary heat exchanger 1, 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, a first cold side ram air output end 1d, a compressor 2, a compressor working medium input end 2a, a compressor working medium output end 2b, a secondary heat exchanger 3, 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, a second cold side ram air output end 3d, a regenerator 4, 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, a first cold side bleed air output end 4d, a condenser 5, 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, a second cold side bleed air output end 5d, a water separator 6, The hot water system comprises a water separator working medium input end 6a, a water separator air-entraining output end 6b, an expander 7, an expander working medium input end 7a, an expander working medium output end 7b, a first gas-liquid heat exchanger 8, a fifth hot side air-entraining input end 8a, a fifth hot side air-entraining output end 8b, a cold side cold source input end 8c, a cold side cold source output end 8d, a second gas-liquid heat exchanger 9, 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, a third cold side ram air output end 9d, a hot water tank 10, a hot water tank working medium input end 10a, a hot water tank working medium output end 10b, a cold water tank 11, a cold water tank working medium input end 11a, a cold water tank working medium output end 11b and a fan 12.

Detailed Description

The technical solution of the present invention will be described in detail below with reference to the accompanying drawings.

As shown in fig. 1, an aircraft environmental control system for supplying hot water by 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 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 respectively connected with the cold water tank 11 and the secondary heat exchanger 3, 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 respectively connected with the secondary heat exchanger 3 and the expander 7, the expander 7 is respectively connected with the heat regenerator 4 and the condenser 5, the condenser 5 is connected with the heat regenerator 4 through the water separator 6, the heat regenerator 4 is connected with the secondary heat exchanger 3, and the outlet of the fan 12 is opposite to the outlet of the primary heat exchanger 1.

The control system of the above embodiment comprises an aircraft environmental control system comprising 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, and a hot water supply cycle. The hot water supply cycle includes 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.

Preferably, the fan 12, the expander 7 and the compressor 2 are coaxially arranged. Of course, other mechanical transmission means may be used to connect the fan 12, the expander 7 and the compressor 2. The expander 7 transfers expansion work to the compressor 2 and the fan 12.

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

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

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

The control method of the control system comprises three processes.

The first process is as follows: leading air of an aircraft engine to enter a control system through a first hot side air-leading input end 1a of a primary heat exchanger 1, carrying out heat exchange on the air-leading and ram air on the cold side of the primary heat exchanger 1, then carrying out heat exchange on the air-leading and cold water in a first gas-liquid heat exchanger 8, pressurizing by a compressor 2, discharging, and flowing into the hot side of a secondary heat exchanger 3 to carry out heat exchange with the ram air; then, the cooled bleed air flows into the heat regenerator 4 and the hot side of the condenser 5 in sequence for recooling; the moisture in the cooled bleed air is separated by the water separator 6, and then the dried bleed air returns to the cold side of the heat regenerator 4 for reheating, then flows into the expander 7 for expansion work and further cooling, and then flows into the cold side of the condenser 5 for reheating, and finally flows into the mixing chamber of the aircraft through the second cold-side bleed air output end 5 d. Flowing out of the second cold-side bleed air output 5d is cold air which supplies the aircraft cabin.

The second process is as follows: the low-temperature and low-pressure ram air outside the cabin of the airplane firstly flows into the cold side of the second gas-liquid heat exchanger 9, flows out of the second gas-liquid heat exchanger 9 after being preheated by hot water, then enters the secondary heat exchanger 3, exchanges heat with high-temperature bleed air at the hot side of the secondary heat exchanger 3, then flows into the primary heat exchanger 1 for heat exchange, and finally is discharged outside the cabin of the airplane through the fan 12.

The third process is as follows: cold water in the cold water tank 11 enters the cold side of the first gas-liquid heat exchanger 8, after heat exchange is carried out between the cold water and bleed air at the hot side of the first gas-liquid heat exchanger 8, the cold water is heated to a set hot water temperature, flows into the hot water tank 10, hot water flows out of the hot water tank 10, enters the hot side of the second gas-liquid heat exchanger 9, exchanges heat with outside-cabin ram air entering the system at the cold side of the second gas-liquid heat exchanger 9, is cooled to the water temperature of the cold water tank, and flows back to the cold water tank 11.

In the first process, the bleed air is used as a heat source, and the bleed air exchanges heat with cold water on the cold side of the first gas-liquid heat exchanger 8 in the first gas-liquid heat exchanger 8, so that the cold water is heated to be hot water.

The control method comprises 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 water flow in the second gas-liquid heat exchanger 9 are controlled to be the same, cold water in the first gas-liquid heat exchanger 8 is heated to hot water by high-temperature bleed air, flows into the second gas-liquid heat exchanger 9 through the hot water tank 10, and after the flushing air is preheated, the water temperature is reduced to the same water temperature in the cold water tank 11, and then returns to the cold water tank 11, so that circulation is formed.

In the self-circulation mode, cold water from the cold water tank 11 enters the first gas-liquid heat exchanger 8, after being heated by high-temperature bleed air, the cold water enters the hot water tank 10 at a constant flow rate, then hot water flows into the second gas-liquid heat exchanger 9 from the hot water tank 10 at the same flow rate, the hot water exchanges heat with low-temperature ram air in the second gas-liquid heat exchanger 9 to reduce the temperature, the water temperature returns to the same temperature as that of the cold water in the cold water tank 11, the cold water flows back into the cold water tank 11, and the circulation is performed sequentially, so that the self-circulation mode is formed. In the self-circulation mode, the inlet temperature of the compressor 2 can be reduced by hot water circulation, thereby improving the working condition of the compressor 2 and reducing 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.

In the hot water supply mode, the water flow speeds in the first gas-liquid heat exchanger 8 and the second gas-liquid heat exchanger 9 are controlled to be different, the water in the first gas-liquid heat exchanger 8 is reduced to flow into the second gas-liquid heat exchanger 9, the water which does not enter the second gas-liquid heat exchanger 9 is stored in the hot water tank 10 in the form of hot water, and hot water is supplied to the airplane.

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

The hot water supply mode can reduce the inlet temperature of the compressor 2, thereby improving the operating condition of the compressor 2 and reducing energy consumption. The self-circulation mode can also reduce the heat exchange temperature difference between the primary heat exchanger 1 and the secondary heat exchanger 3, thereby reducing the heat exchange energy dissipation. The hot water quantity participating in hot water circulation is reduced by simply adjusting the water flow of the two gas-liquid heat exchangers, and the hot water is stored in the hot water tank 10 in the form of domestic hot water, so that the hot water can be supplied to aircraft users for use. Therefore, the invention can obtain hot water in the airplane more simply, flexibly and controllably by controlling the water flow.

The embodiment of the invention solves the problem of overlarge energy consumption caused by an aircraft environment control system and an aircraft hot water supply mode. After hot water circulation is added in the system, the circulating hot water preheats ram air, and the heat exchange temperature difference between the primary heat exchanger 1 and the secondary heat exchanger 3 is reduced, so that the heat exchange energy consumption is reduced; secondly, the hot water circulation is added, the temperature of the air suction inlet of the compressor 2 is reduced, the working condition of the compressor 2 is improved, and the energy consumption of the compressor 2 is further reduced. The communication among all parts of the airplane environment control system is built, and the saved heat is utilized to heat water for the airplane. This application has utilized original elementary heat exchanger and secondary heat transfer because the too big energy that dissipates of heat transfer temperature difference adds hot water.

The high-temperature and high-pressure bleed air is used as a heat source of an aircraft environmental control system. The method comprises the steps that high-temperature and high-pressure bleed air generated by an engine enters a system from the hot side of a primary heat exchanger 1, enters a first gas-liquid heat exchanger 8 for cooling again after heat exchange of the primary heat exchanger 1, enters a compressor 2 for pressurizing and heating after the cooled bleed air, flows into a secondary heat exchanger 3 for cooling, flows into the hot side of a heat regenerator 4 for heat exchange, then enters a condenser 5 for condensation, and then enters a water separator 6 for moisture separation. And the dry bleed air flows out of the water separator 6, enters the cold side of the heat regenerator 4 to be heated, then flows into the expander 7 to do work expansion, the temperature is reduced, and finally the bleed air flows into the cold side of the condenser 5 to be heated, meets the cooling requirement of the passenger cabin and enters the airplane mixing chamber.

Low-temperature ram air outside the cabin is used as a cold source of an airplane environment control system, firstly enters the system from the cold side of the second gas-liquid heat exchanger 9, exchanges heat with hot water in the second gas-liquid heat exchanger 9, then rises in temperature, enters the cold side of the secondary heat exchanger 3 for heat exchange, takes away heat of bleed air at the hot side of the secondary heat exchanger 3, enters the cold side of the primary heat exchanger 1 for heat exchange of the bleed air at high temperature, and then is discharged outside the cabin through the fan 12. There are three working fluids in the system of the present application, namely: ram air outside the cabin, high temperature induced gas and water. Hot water supply on the airplane and cold air supply in the passenger cabin of the airplane are realized through the circulation of the three working media.

The self-circulation mode of the system is that the cold side of the first gas-liquid heat exchanger 8 and the hot side of the second gas-liquid heat exchanger 9 are connected in series, cold water is pumped into the cold side of the first gas-liquid heat exchanger 8 from the cold water tank 11, and after air-entraining heat exchange of the hot side of the first gas-liquid heat exchanger 8, the cold water is heated and flows into the hot side of the second gas-liquid heat exchanger 9 to preheat low-temperature ram air, so that the hot water flows into the cold water tank 11 after being cooled to the temperature of the cold water tank 11.

In a hot water supply mode of the system, the cold side of the first gas-liquid heat exchanger 8 and the hot side of the second gas-liquid heat exchanger 9 are connected in series, cold water is pumped into the cold side of the first gas-liquid heat exchanger 8 from the cold water tank 11, after bleed air at the hot side of the first gas-liquid heat exchanger 8 exchanges heat, the flow of hot water entering the second gas-liquid heat exchanger 9 is adjusted after the cold water is heated, the hot water entering the second gas-liquid heat exchanger 9 is reduced for exchanging heat, and the hot water is stored in the hot water tank 10 in a domestic hot water mode.

The water 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 performance of the airplane environment control system and supplying hot water for the airplane. The system of the application comprises a hot water circulating system, the hot water in the circulation preheats the ram air outside the cabin entering the system, and the cold water in the circulation cools the high-temperature bleed air discharged from the hot side of the primary heat exchanger. Therefore, the excessive energy dissipation caused by the excessive heat exchange temperature difference between the primary heat exchanger and the secondary heat exchanger can be reduced, and the suction temperature at the inlet of the compressor can be reduced, so that the operation working condition of the compressor is improved, and the operation energy consumption is reduced. The hot water circulation in this application system still can carry out simple convenient ground flow control, reduces hydrothermal outflow in the hot-water cylinder to the hot-water mode of life is stored.