Aero-engine high-altitude environment adjusting system

Abstract

The embodiment of the specification provides an aero-engine high-altitude environment adjusting system, comprising: a mixer, a low-temperature constant-pressure gas supply pipe G1 and a high-temperature constant-pressure gas supply pipe G2, low-temperature constant-pressure gas enters the mixer through the low-temperature constant-pressure gas supply pipe G1, and high-temperature constant-pressure gas enters the mixer through the high-temperature constant-pressure gas supply pipe G2; a high-altitude test cabin, an air inlet pipe G3 and an exhaust pipe G4, the high-altitude test cabin takes in air from the mixer through the air inlet pipe G3 and discharges exhaust through the exhaust pipe G4; a gas supply amount control assembly; a gas extraction amount control assembly; a temperature control assembly. The adjusting is performed through fixed gas supply flow, pressure and temperature, and fixed gas extraction pressure and flow. All the flow, pressure and temperature are self-balanced through the adjusting system, and the gas source system or the air compressor system is not needed for adjusting, so that the design of the gas source system is simplified and the cost is reduced. Meanwhile, the adjusting control can be performed through an automatic control system.

Description

TECHNICAL FIELD

[0001] The present specification relates to the technical field of high-altitude test of an aero-engine, in particular to a high-altitude environment adjusting system of an aero-engine. BACKGROUND

[0002] A large number of high-altitude tests need to be carried out on an aero-engine, and the high-altitude test refers to simulating the pressure and temperature environment of an aircraft in flight on a test bench, and ensuring sufficient air for engine intake. Therefore, the high-altitude environment adjusting system is used to adjust the pressure and temperature of the front cabin of the high-altitude test cabin under a certain air intake flow (the air flow is greater than the air flow required by the engine), so as to meet the requirements of the total pressure and total temperature of the engine inlet (the total pressure and total temperature refer to the pressure and temperature of the atmosphere after being compressed and stagnated by the flight speed), and the pressure of the rear cabin meets the requirements of the environmental pressure of the engine exhaust port (i.e. the pressure corresponding to the height to be simulated). The high-altitude environment is often in a cabin or a closed space, and the environmental pressure (absolute pressure 2kPa-100kPa) of the cabin or space is lower than the ground atmospheric pressure, and the environmental temperature (-80℃-71℃) is also lower than the ground atmospheric temperature.

[0003] The air flow sucked by the aero-engine at different speeds will be different, that is, the air flow sucked will change with the change of the speed. Therefore, a set of adjusting system is needed to keep the pressure of the front and rear cabins stable. At the same time, because the change of the flow changes the change of the cold gas and hot gas mixing, if the adjustment is not good, it will also lead to the change of the temperature, so a set of adjusting system is also needed to keep the temperature stable. After the air is burned and discharged by the engine, the outlet exhaust gas temperature is often very high (1000℃), which will cause serious damage to the rear-end air extraction equipment and is not conducive to the stability of the rear-end pressure, so a temperature reduction and pressure balance adjusting system is needed.

[0004] The parameters of each test working condition of the high-altitude test change in a large range, so a flexible and stable and reliable working condition adjusting system is needed. The currently used adjusting device is expensive and difficult to adjust, and there is a lack of device suitable for light turbojet and turbofan engines for high-altitude test, which cannot meet the requirements of the adjusting system of the inlet and outlet pressure and temperature of the engine. SUMMARY

[0005] Therefore, the embodiment of the present specification provides a high-altitude environment adjusting system of an aero-engine, so as to achieve self-balancing of the flow, pressure and temperature adjusting system, without the need for a gas source system or an air compressor system for adjustment, simplifying the design of the gas source system, and achieving the purpose of reducing the cost.

[0006] The embodiment of the present specification provides the following technical solutions:

[0007] An aero-engine high-altitude environment adjusting system comprises:

[0008] a mixer, a low-temperature constant-pressure gas supply pipe G1 and a high-temperature constant-pressure gas supply pipe G2, the low-temperature constant-pressure gas enters the mixer through the low-temperature constant-pressure gas supply pipe G1, and the high-temperature constant-pressure gas enters the mixer through the high-temperature constant-pressure gas supply pipe G2;

[0009] a high-altitude test cabin, an air inlet pipe G3 and an air outlet pipe G4, the high-altitude test cabin takes in air from the mixer through the air inlet pipe G3 and discharges air through the air outlet pipe G4;

[0010] a gas supply amount control assembly, the gas supply amount control assembly being arranged between the mixer and the high-altitude test cabin;

[0011] a gas extraction amount control assembly, the gas extraction amount control assembly being arranged between the high-altitude test cabin and the air outlet pipe G4;

[0012] a temperature control assembly, the temperature control valve assembly being arranged on the low-temperature constant-pressure gas supply pipe G1 and the high-temperature constant-pressure gas supply pipe G2.

[0013] Further, the temperature control assembly comprises:

[0014] a low-temperature adjusting valve T1, the low-temperature adjusting valve T1 being arranged on the low-temperature constant-pressure gas supply pipe G1, and the low-temperature constant-pressure gas being communicated to the mixer through the low-temperature adjusting valve T1;

[0015] a high-temperature adjusting valve T2, the high-temperature adjusting valve T2 being arranged on the high-temperature constant-pressure gas supply pipe G2, and the high-temperature constant-pressure gas being communicated to the mixer through the high-temperature adjusting valve T2.

[0016] Further, the high-altitude test cabin comprises a front cabin and a rear cabin, the engine being placed in the rear cabin, and the front cabin being connected to the air inlet of the engine through a front-rear cabin partition.

[0017] Further, the gas supply amount control assembly comprises:

[0018] a pressure adjusting valve P1, the pressure adjusting valve P1 being arranged between the mixer and the front cabin;

[0019] a pressure adjusting valve P2, the pressure adjusting valve P2 being arranged between the air inlet pipe G3 and the air outlet pipe G4;

[0020] a pressure adjusting valve P3, the pressure adjusting valve P3 being arranged between the front cabin and the air outlet pipe G4.

[0021] Further, the gas extraction amount control assembly comprises:

[0022] a pressure adjusting valve P4, the pressure adjusting valve P4 being arranged between the rear cabin and the air outlet pipe G4;

[0023] A pressure regulating valve P5 is arranged between the exhaust pipe G4 and the high-temperature constant-pressure gas supply pipe G2.

[0024] A pressure regulating valve P6 is arranged between the exhaust pipe G4 and the low-temperature constant-pressure gas supply pipe G1.

[0025] Further, the aero-engine high-altitude environment regulating system further comprises a bleed air amount control assembly, which comprises:

[0026] The low-temperature bleed air valve F1, the high-temperature bleed air valve F2 and the exhaust tower, the low-temperature constant-pressure gas enters the exhaust tower through the low-temperature bleed air valve F1, and the high-temperature constant-pressure gas enters the exhaust tower through the high-temperature bleed air valve F2.

[0027] Further, the aero-engine high-altitude environment regulating system further comprises a bleed air amount control assembly, which comprises:

[0028] The bleed air valve B1 and the intake tower, the intake tower is connected to the exhaust pipe G4 through the bleed air valve B1.

[0029] Further, the aero-engine high-altitude environment regulating system further comprises a heat exchanger, one end of the heat exchanger is in communication with the rear cabin, and the other end of the heat exchanger is connected to the exhaust pipe G4 through the bleed air amount control assembly.

[0030] Further, the gas supply amount control assembly, the bleed air amount control assembly and the temperature control assembly are connected to the automatic control system.

[0031] Further, the bleed air amount control assembly is connected to the automatic control system.

[0032] Compared with the prior art, the above at least one technical solution adopted by the embodiments of the present application can achieve at least the following beneficial effects:

[0033] The regulating system of the present application is regulated by fixed gas supply flow, pressure and temperature, and fixed bleed air pressure and flow, all the flow, pressure and temperature are self-balanced by the regulating system, and there is no need to adjust the air source system or the air compressor system, thereby simplifying the design of the air source system and reducing the cost. The internal self-balancing of the regulating system is controlled by the valves, the adjustment range of each valve is clear and known, and the automatic control system is convenient for adjustment and control. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0035] Figure 1 is a schematic diagram of the overall structure of an engine high-altitude environment adjustment system according to an embodiment of the present application.

[0036] Reference signs: 1, mixer; 2, high-altitude test chamber; 3, front chamber; 4, rear chamber; 5, heat exchanger; 6, air inlet tower; 7, air outlet tower. DETAILED DESCRIPTION

[0037] The embodiments of the present application will be described in detail below with reference to the drawings.

[0038] The above embodiments are only some of the embodiments of the present application, and not all of the embodiments of the present application. The present application can also be implemented or applied in other different specific embodiments, and each detail in the specification can be modified or changed based on different views and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0039] It should be noted that the various aspects described below are within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms and that any specific structure and / or function described herein is merely illustrative. Based on the teachings herein one skilled in the art should appreciate that an aspect described herein can be implemented independently of any other aspects and that an aspect described herein can be implemented both as any number of software and / or hardware structures and as any number of processes and / or operations. For example, an aspect can be implemented as a software program running on hardware that can process information such as, for example, information stored in a computer-readable storage medium. As another example, an aspect can be implemented as a software program running on hardware that can process information such as, for example, information stored in a computer-readable storage medium.

[0040] It should also be noted that the drawings included in the present disclosure are included to illustrate potentially complex structures associated with the application. However, the drawings are included to illustrate one possible implementation of the present application and that in no way limits the scope of the application to the features depicted. It should be apparent to those of skill in the art that structures other than the ones depicted can also be utilized and that

[0041] In addition, in the following description, specific details are provided to thoroughly understand the examples. However, one of ordinary skill in the art will understand that the described aspects can be practiced without these specific details.

[0042] The technical solutions provided by the embodiments of the present application are described below with reference to the drawings.

[0043] With reference to Figure 1 The high-altitude environment adjusting system of the embodiment of the present application mainly comprises a mixer 1, a high-altitude test cabin 2, a heat exchanger 5, a low-temperature constant-pressure gas supply pipe G1, a high-temperature constant-pressure gas supply pipe G2, a gas inlet pipe G3, a gas outlet pipe G4, a gas extraction amount control assembly, a gas emission amount control assembly, a gas extraction and supply control assembly and a temperature control assembly. The high-altitude test cabin 2 comprises a front cabin 3 and a rear cabin 4. The temperature control assembly comprises a low-temperature adjusting valve T1 and a high-temperature adjusting valve T2. The gas supply amount control assembly comprises a pressure adjusting valve P1, a pressure adjusting valve P2 and a pressure adjusting valve P3. The gas extraction amount control assembly comprises a pressure adjusting valve P4, a pressure adjusting valve P5 and a pressure adjusting valve P6. The gas emission amount control assembly comprises a low-temperature gas emission valve F1, a high-temperature gas emission valve F2 and a gas emission tower 7. The gas extraction and supply control assembly comprises a gas extraction and supply valve B1 and a gas inlet tower 6.

[0044] The test engine is installed in the rear cabin 4 and inhales air from the front cabin 3. The high-temperature constant-pressure gas supply pipe G2 delivers a high-temperature constant-pressure gas source to the mixer 1 through the high-temperature adjusting valve T2, and the low-temperature constant-pressure gas supply pipe G1 delivers a low-temperature constant-pressure gas source to the mixer 1 through the low-temperature adjusting valve T1. The mixer 1 is connected to the front cabin 3 through the gas inlet pipe G3 and passes through the pressure adjusting valve P1. The mixer 1 is connected to the front cabin 3 through the pressure adjusting valve P1, the pressure adjusting valve P2 and the pressure adjusting valve P3. The front cabin 3 and the rear cabin 4 are communicated, and the rear cabin 4 passes through the heat exchanger 5, and then passes through the adjusting valve P4, the gas extraction and supply valve P5 and the gas extraction and supply valve P6 to be exhausted. The high-temperature constant-pressure gas supply pipe G2 is connected to the gas emission tower 7 through the high-temperature gas emission valve F2, and the low-temperature constant-pressure gas supply pipe G1 is connected to the gas emission tower 7 through the low-temperature gas emission valve F1. The gas outlet pipe G4 is connected to the gas inlet tower 6 through the gas extraction and supply valve B1.

[0045] Specifically, the high-temperature constant-pressure gas is high-temperature gas flowing out of a gas source, the temperature of which is higher than 30℃, the pressure of which is higher than 2bar, and the flow of which is more than 50% of the maximum flow of the engine, so that the gas supply flow, pressure and temperature are kept stable.

[0046] Specifically, the low-temperature constant-pressure gas is low-temperature gas flowing out of a gas source, the temperature of which is lower than -20℃, the pressure of which is higher than 1bar, and the flow of which is more than 50% of the maximum flow of the engine, so that the gas supply flow, pressure and temperature are kept stable.

[0047] Specifically, the mixer 1 mixes the high-temperature gas and the low-temperature gas to realize uniform outlet temperature, and the total gas flow is about 120% of the maximum flow of the engine.

[0048] Specifically, the forward compartment 3 is the front half of the high-altitude test compartment 2, with its exit being a bulkhead connecting the front and rear compartments, through which the engine's air intake is located. The engine is installed in the rear compartment 4 and draws air from the forward compartment 3. The main function of the forward compartment 3 is to stabilize and simulate the engine's inlet pressure and temperature, as well as to homogenize the pressure and temperature. The test engine is installed in the rear compartment 4, which simulates the engine's outlet pressure and simultaneously removes the heat generated during engine operation, maintaining the pressure within the rear compartment 4 within the engine's tolerance range.

[0049] Specifically, heat exchanger 5 is usually water-cooled, but other cooling methods can also be used to cool the high-temperature exhaust gas from the engine to a temperature range that the rear end can withstand (below 500°C).

[0050] Specifically, the self-balancing mechanism in this embodiment of the invention is achieved according to the following principle: Figure 1 As shown, high-temperature constant-pressure gas supply and low-temperature constant-pressure gas supply are two different types of gas sources. The temperature, pressure, and flow rate of the gas flowing out from both sources remain constant, indicating that the gas supply capacity is constant. Negative-pressure constant-pressure pumping indicates that the pumping capacity of the pump is constant. Because the parameters of various test conditions in the high-altitude test chamber 2 vary greatly, it is necessary to simulate different temperatures, pressures, and flow rates. However, the input and output of this system are constant, and the simulation of different environments can only be achieved through internal adjustments within the system to reach an internal equilibrium state.

[0051] In some implementations, such as when using the high-altitude test chamber 2 for high-pressure, low-flow-rate testing, the gas supply capacity is constant. However, if the flow rate is too high for low-flow-rate testing, the regulating system of this embodiment can release excess gas by adjusting the low-temperature vent valve F1 and the high-temperature vent valve F2. If it is necessary to adjust the temperature of the high-altitude test chamber 2, the inflow ratio of high-temperature and low-temperature gas is controlled by adjusting the low-temperature regulating valve T1 and the high-temperature regulating valve T2, so that the mixer 1 mixes gases of different temperatures that flow into the high-altitude test chamber 2. Then, by adjusting the pressure regulating valve P1 to decrease and P2 to increase, the gas pressure in the front chamber 3 is increased. The pressure in the front chamber 3 of the high-altitude test chamber 2 can also be changed by adjusting the pressure regulating valve P3. Since the exhaust pumping capacity of the pumping unit is fixed, if the exhaust flow of the front compartment 4 is small, the pumping unit cannot work normally. This can be achieved by adjusting the pressure regulating valve P4, and then adjusting the pressure regulating valves P5 and P6 to match the pressure of the regulating valve P4, so as to replenish the exhaust and maintain the normal operation of the pumping unit. If the supply of replenished air is insufficient, replenishment air can be achieved by opening the exhaust replenishment valve B1.

[0052] In some embodiments, when the low-pressure large-flow test is performed using the high-altitude test chamber 2, the gas supply capacity is certain, and after the high-pressure small-flow test is performed, the low-pressure large-flow test is performed in the same chamber. The adjusting system can increase the gas flow by reducing or closing the low-temperature exhaust valve F1 and the high-temperature exhaust valve F2, control the inflow ratio of the high-temperature gas and the low-temperature gas by adjusting the low-temperature adjusting valve T1 and the high-temperature adjusting valve T2, and make the mixer 1 mix different gas temperatures to flow into the high-altitude test chamber 2. Since the gas supply pressure is generally greater than the test pressure, the gas pressure entering the front chamber 3 is reduced by increasing the pressure adjusting valve P1 and reducing the pressure adjusting valve P2. The front chamber 3 can also change the pressure of the front chamber 3 by adjusting the pressure adjusting valve P3. Since the air extraction unit has a certain air extraction capacity, if the front chamber 4 has a low exhaust pressure, the air extraction unit cannot work normally, and the pressure of the front chamber 4 can be increased by adjusting the pressure adjusting valve P4. When the large-flow test is performed, the adjusting pressure adjusting valve P5, the adjusting pressure adjusting valve P6, and the air extraction and air supply valve B1 do not need to be adjusted.

[0053] In some embodiments, when the medium-pressure medium-flow test is performed using the high-altitude test chamber 2, since the gas supply capacity is certain, when the test gas supply pressure and flow are too high, the adjusting system can vent the excess gas by adjusting the low-temperature exhaust valve F1 and the high-temperature exhaust valve F2. The inflow ratio of the high-temperature gas and the low-temperature gas is controlled by adjusting the low-temperature adjusting valve T1 and the high-temperature adjusting valve T2, different gas temperatures are mixed by the mixer 1 to flow into the high-altitude test chamber 2, and the gas pressure entering the front chamber 3 is reduced by increasing the pressure adjusting valve P1 and reducing the pressure adjusting valve P2. The high-altitude test chamber 2 can also change the pressure of the front chamber 3 by adjusting the pressure adjusting valve P3. Since the air extraction unit has a certain air extraction capacity, if the rear chamber 4 has a low exhaust pressure and flow, the air extraction unit cannot work normally, the pressure can be increased by adjusting the pressure adjusting valve P4, and the exhaust gas is air-supplied to maintain the normal work of the air extraction unit by adjusting the pressure adjusting valve P5 and the pressure adjusting valve P6 to be consistent with the pressure of the pressure adjusting valve P4. At this time, the air extraction and air supply valve B1 is in a closed state.

[0054] In some embodiments, for intake temperature adjustment, there are two cases: when the engine intake temperature is lower than the atmospheric temperature during the test, the cold gas (temperature range: generally -20°C to -70°C, flow: 5 kg / s to 20 kg / s) and the dry normal temperature gas (temperature range: generally 30°C to 40°C, flow: 5 kg / s to 20 kg / s) of the gas source system are mixed and adjusted; when the engine intake temperature is higher than the atmospheric temperature during the test, the hot gas (temperature range: generally 120°C to 140°C, flow: 5 kg / s to 20 kg / s) and the normal temperature gas of the gas source system are mixed and adjusted.

[0055] For example, low temperature regulation, the compressed air provided by the air supply system enters the mixer 1 through the low temperature constant pressure air pipe (for example, the temperature of the cold air is -70℃, and the total flow is 20kg / s) and the high temperature constant pressure air pipe (for example, the temperature of the dry normal temperature air is 30℃, and the total flow is 10kg / s), and the temperature of the outlet of the mixer 1 is -36℃ and the flow is 30kg / s. In the test, the temperature of the air supply of the mixer 1 is basically stable, and the temperature of the outlet of the mixer 1 (the inlet temperature of the high altitude test chamber 2) can be regulated by adjusting the opening degrees of the low temperature constant pressure air supply temperature regulating valve T1 and the high temperature constant pressure air supply temperature regulating valve T2, or by adjusting the low temperature air exhaust valve F1 and the high temperature air exhaust valve F2 to change the flow of the two air supplies, and then uniformly mixing in the mixer 1, so as to quickly realize the regulation of the engine inlet air temperature. The temperature of the exhaust gas of the engine is high, and the temperature of the exhaust gas is reduced after passing through the heat exchanger 5, so as to realize the regulation of the exhaust gas temperature.

[0056] In some embodiments, for pressure regulation, the gas at the outlet of the mixer 1 enters the high altitude test chamber 2 through the air supply pressure regulating valve P1 and the air supply pressure regulating valve P2 to control the flow of the gas entering the high altitude test chamber 2, and the air supply pressure regulating valve P3 controls the pressure difference before and after the high altitude test chamber 2, and the pressure regulating valve P1, the pressure regulating valve P2 and the pressure regulating valve P3 together realize the quick and stable regulation of the pressure of the front chamber 3. The regulation of the pressure of the rear chamber 4 is to regulate the exhaust environment pressure of the test engine, which is mainly realized by the exhaust pressure regulating valve P4 and the air exhaust and air supply valve P5 and the air exhaust and air supply valve P6. When the state of the engine changes instantaneously, the state change is extremely violent, and the air flow of the engine can change by 80% to 100%, at this time, the inlet air pressure control system feeds forward the compensation of the inlet air pressure according to the state change of the engine, mainly by quickly opening and closing the pressure regulating valve P1 and the pressure regulating valve P2 to quickly change the flow of the high altitude test chamber 2 and the flow of the bypass, so as to realize the transient regulation of the inlet air pressure of the engine.

[0057] It should be noted that the inlet air flow of the engine is 4kg / s when the engine is at slow speed, and the maximum state is 23kg / s, and during the regulation process, the opening degree of the pressure regulating valve P1 is about 20% when the engine is at slow speed, and the opening degree of the pressure regulating valve P2 is about 80%, when accelerating, the pressure regulating valve P1 is quickly opened to the given position, the pressure regulating valve P2 is quickly closed to the given position, and a large amount of air enters the high altitude test chamber 2 to supply the engine. When simulating different altitudes, the exhaust air amount is mainly controlled by the exhaust pressure regulating valve P4 and the air exhaust and air supply valve P5 and the air exhaust and air supply valve P6, and the air supply amount is controlled by the air supply pressure regulating valve P1, the air supply pressure regulating valve P2 and the pressure difference regulating valve P3, and the like, to realize the regulation of the simulated altitude of the engine.

[0058] In some embodiments, the pressure regulating valve P1, the pressure regulating valve P2, the pressure regulating valve P3, the pressure regulating valve P4, the pressure regulating valve P5, the pressure regulating valve P6, the low-temperature regulating valve T1, the high-temperature regulating valve T2, the low-temperature bleeder valve F1, the high-temperature bleeder valve F2, the low-temperature constant-pressure gas supply pipe G1, the high-temperature constant-pressure gas supply pipe G2, and the air extraction and air supply valve B1 can be controlled by an automatic control system.

[0059] Therefore, the air supply flow rate, pressure, and temperature inside the high-altitude environment regulating system of the embodiments of the present application can be self-balanced, and the air source system or the air compressor system does not need to be adjusted, thereby simplifying the design of the air source system and reducing the cost. The regulating range of each valve in the above structure is clear, which facilitates the programming of the automatic control system, so that the air supply flow rate, pressure, and temperature can be dynamically controlled by the computer program, and the flow rate, pressure, and temperature can be controlled, thereby meeting the regulating requirements of the engine inlet and outlet pressure and temperature, and improving the accuracy of the high-altitude test.

[0060] Each of the embodiments in the specification is described in a progressive manner, and the same or similar parts of each of the embodiments can be referred to each other. Each of the embodiments focuses on the difference from other embodiments. In particular, for the method embodiments described later, since the method embodiments are corresponding to the system, the description is relatively simple, and the relevant parts can be referred to the part of the system embodiment.

[0061] The above merely describes the specific embodiments of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed in the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft engine high altitude environment conditioning system, characterized by, The system comprises: a mixer (1), a low-temperature constant-pressure gas supply pipe G1 and a high-temperature constant-pressure gas supply pipe G2, the low-temperature constant-pressure gas entering the mixer (1) through the low-temperature constant-pressure gas supply pipe G1, and the high-temperature constant-pressure gas entering the mixer (1) through the high-temperature constant-pressure gas supply pipe G2; an altitude test chamber (2), an air inlet pipe G3 and an air outlet pipe G4, the altitude test chamber (2) taking in air from the mixer (1) through the air inlet pipe G3 and discharging air through the air outlet pipe G4; a gas supply amount control assembly arranged between the mixer (1) and the altitude test chamber (2); a gas extraction amount control assembly arranged between the altitude test chamber (2) and the air outlet pipe G4; a temperature control assembly arranged on the low-temperature constant-pressure gas supply pipe G1 and the high-temperature constant-pressure gas supply pipe G2; the temperature control assembly comprising: a low-temperature regulating valve T1 arranged on the low-temperature constant-pressure gas supply pipe G1, through which the low-temperature constant-pressure gas is communicated to the mixer (1); a high-temperature regulating valve T2 arranged on the high-temperature constant-pressure gas supply pipe G2, through which the high-temperature constant-pressure gas is communicated to the mixer (1); the altitude test chamber (2) comprising a front chamber (3) and a rear chamber (4); the gas supply amount control assembly comprising: a pressure regulating valve P1 arranged between the mixer (1) and the front chamber (3); a pressure regulating valve P2 arranged between the air inlet pipe G3 and the air outlet pipe G4; a pressure regulating valve P3 arranged between the front chamber (3) and the air outlet pipe G4; the gas extraction amount control assembly comprising: a pressure regulating valve P4 arranged between the rear chamber (4) and the air outlet pipe G4; a pressure regulating valve P5 arranged between the air outlet pipe G4 and the high-temperature constant-pressure gas supply pipe G2; a pressure regulating valve P6 arranged between the air outlet pipe G4 and the low-temperature constant-pressure gas supply pipe G1; the aero-engine altitude environment adjusting system further comprising a gas discharge amount control assembly, which comprises: a low-temperature gas discharge valve F1, a high-temperature gas discharge valve F2 and an exhaust tower (7), through which the low-temperature constant-pressure gas enters the exhaust tower (7), and through which the high-temperature constant-pressure gas enters the exhaust tower (7); the aero-engine altitude environment adjusting system further comprising a gas extraction and air supply control assembly, which comprises: a gas extraction and air supply valve B1 and an air inlet tower (6) connected to the air outlet pipe G4 through the gas extraction and air supply valve B1; the altitude environment adjusting system can keep the gas supply flow, pressure and temperature self-balanced without the need for adjustment of the gas source system or the air compressor system.

2. The aircraft engine high altitude environment conditioning system of claim 1, wherein, The rear chamber (4) is arranged to place the engine, and the front chamber (3) is connected to the air inlet of the engine through a front-rear chamber partition.

3. The aircraft engine high altitude environment conditioning system of claim 1, wherein, The aero-engine high-altitude environment adjusting system further comprises a heat exchanger (5), one end of the heat exchanger (5) is communicated with the rear cabin (4), and the other end of the heat exchanger (5) is connected with the exhaust pipe G4 through the air extraction amount control assembly.

4. The aircraft engine high altitude environment conditioning system in accordance with Claim 1, wherein, The air supply amount control assembly, the air extraction amount control assembly and the temperature control assembly are connected with an automatic control system.

5. The aircraft engine high altitude environment conditioning system in accordance with Claim 1, wherein, The air extraction and air supply control assembly is connected with the automatic control system.

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