High-altitude environment simulation device for general aero-engine

Abstract

The invention discloses a general aero-engine high-altitude environment simulation device, and relates to the technical field of aviation tested engine tests, the general aero-engine high-altitude environment simulation device comprises a fresh air system, a refrigerating unit and a tested engine, the output end of the fresh air system is provided with a connecting pipeline, and one side of the connecting pipeline is provided with the refrigerating unit communicated with the interior of the connecting pipeline; an air inlet and outlet proportional valve is arranged on the inner side wall, close to the refrigerating unit, of the connecting pipeline, a pipeline heating device is arranged on the outer wall, close to the air inlet and outlet proportional valve, of the connecting pipeline, and a first pressure stabilizing tank is arranged on the side, away from the pipeline heating device, of the connecting pipeline. According to the device, through cooperative control of the intake and exhaust proportional valve and the vacuum pump unit, precise simulation that the pressure fluctuation range is smaller than or equal to + / -1% and the temperature deviation is smaller than or equal to + / -1 DEG C at the height of 0-12000 meters is achieved, and the airworthiness certification standard is met.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengine test under test, and specifically to a high-altitude environment simulation device for general aviation engines. Background Technique

[0002] High-altitude simulation test is a reliable way to verify the high-altitude performance of aeroengines under test, as well as their reliability and efficiency in extreme environments, and it plays a dominant role in the entire development test. Traditional verification methods rely on flight tests, but they are costly, time-consuming and pose high safety risks. High-altitude simulation test can significantly improve the R & D efficiency and safety by reproducing high-altitude environments (such as low temperature and low pressure) through ground equipment.

[0003] However, the existing high-altitude environment simulation devices for general aviation engines have the following problems during use: the number of traditional domestic special high-altitude simulation test benches is limited, and most of them serve large military / commercial engines under test. The test resources in the general aviation field are seriously insufficient and scarce; the investment in newly built high-altitude test benches is huge; the dependence on imported equipment is high and the maintenance cost is high; most of the existing test benches are of fixed design and it is difficult to flexibly adapt to the test requirements of different models of general engines under test. Summary of the Invention

[0004] The purpose of the present invention is to provide a high-altitude environment simulation device for general aviation engines to solve the related problems raised in the above background technique.

[0005] To achieve the above purpose, the present invention provides the following technical solution: A high-altitude environment simulation device for general aviation engines, including a fresh air system, a refrigeration unit and an engine under test. The output end of the fresh air system is equipped with a connecting pipeline. One side of the connecting pipeline is provided with a refrigeration unit communicated with its interior. The inner side wall of the connecting pipeline close to the refrigeration unit is provided with an intake and exhaust ratio valve. The outer wall of the connecting pipeline close to the intake and exhaust ratio valve is provided with a pipeline heating device. One side of the connecting pipeline far from the pipeline heating device is provided with a first pressure stabilizing tank, and the input end and output end of the first pressure stabilizing tank are respectively connected to the connecting pipeline and one end of the engine under test. One side of the connecting pipeline is provided with a vacuum pump unit communicated with its interior through a check valve, and heat exchangers are respectively arranged on both sides of the vacuum pump unit.

[0006] The high-altitude environment simulation device for general aviation engines provided by this technical solution is composed of a dehumidifier and a pipeline for the fresh air system.

[0007] The high-altitude environment simulation device for general aviation engines provided by this technical solution is composed of a compressor, a condenser, an evaporator and a pipeline for the refrigeration unit.

[0008] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. A tail gas treatment device is arranged at the tail gas end of the engine under test through a connecting pipeline. A second pressure stabilizing tank connected to a vacuum pump unit is installed at one end of the connecting pipeline close to the tail gas treatment device.

[0009] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. The tail gas treatment device is composed of a filter and a pipeline.

[0010] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. The refrigeration unit provides cold energy for the fresh air system to realize the dry air required for the temperature environment of 15°C to -60°C.

[0011] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. A control system is arranged on one side of the engine under test.

[0012] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. The control system is composed of a computer.

[0013] A device for simulating high-altitude environment of general aviation engines provided by this technical solution. One ends of the refrigeration unit, the heat exchanger and the vacuum pump unit are respectively connected to the chiller through a circulation pipe.

[0014] Compared with the prior art, the present invention provides a device for simulating high-altitude environment of general aviation engines, having the following beneficial effects: 1. After the gas enters the tail gas treatment device for purification treatment in the present invention, it enters the second pressure stabilizing tank for secondary pressure stabilization, and finally is pumped out by the vacuum pump unit. The vacuum pump unit operates continuously to ensure that the entire system is maintained within the environmental pressure range required by the set altitude. The deviation part is adjusted by the intake and exhaust proportional valve to meet the pressure requirements of high-altitude simulation. Through the coordinated control of the intake and exhaust proportional valve and the vacuum pump unit, accurate simulation with a pressure fluctuation range of ≤±1% and a temperature deviation of ≤±1°C at an altitude of 0 - 12,000 meters is achieved, meeting the airworthiness certification standards, and achieving the purpose of saving aviation engine high-altitude simulation test resources, reducing duplicate construction, and reducing the development cost of general aviation engines under test. Description of the Drawings

[0015] Figure 1 It is a schematic diagram of the internal circuit structure of the present invention; Figure 2 It is a front view structure schematic diagram of the present invention.

[0016] In the figure: 1. Fresh air system; 2. Refrigeration unit; 3. Vacuum pump unit; 4. Inlet and exhaust ratio valve; 5. First pressure stabilizing tank; 6. Connecting pipeline; 7. Pipeline heating device; 8. Chiller; 9. Control system; 10. Heat exchanger; 11. Second pressure stabilizing tank; 12. Tail gas treatment device filter and pressure stabilizing tank. Detailed implementation mode

[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0018] Example 1, as Figure 1-2As shown in the figure, the present invention provides a technical solution: a high-altitude environment simulation device for a general aviation engine, including a fresh air system 1, a refrigeration unit 2, and the engine to be tested. It is characterized in that: a connecting pipeline 6 is installed at the output end of the fresh air system 1, and a refrigeration unit 2 communicating with its interior is arranged on one side of the connecting pipeline 6. An intake and exhaust proportional valve 4 is arranged on the inner side wall of the connecting pipeline 6 close to the refrigeration unit 2. A pipeline heating device 7 is arranged on the outer wall of the connecting pipeline 6 close to the intake and exhaust proportional valve 4. A first pressure stabilizing tank 5 is arranged on one side of the connecting pipeline 6 away from the pipeline heating device 7. The input end and the output end of the first pressure stabilizing tank 5 are respectively connected to the connecting pipeline 6 and one end of the engine to be tested. A vacuum pump unit 3 communicating with its interior is arranged on one side of the connecting pipeline 6 through a check valve. Heat exchangers 10 are respectively arranged on both sides of the vacuum pump unit 3. The fresh air system 1 is composed of a dehumidifier and pipelines. The refrigeration unit 2 is composed of a compressor, a condenser, an evaporator, and pipelines. A tail gas treatment device 12 is arranged at the tail gas end of the engine to be tested through the connecting pipeline 6. A second pressure stabilizing tank 11 connected to the vacuum pump unit 3 is installed at one end of the connecting pipeline 6 close to the tail gas treatment device 12. The tail gas treatment device 12 is composed of a filter and pipelines. The refrigeration unit 2 provides cold air for the fresh air system 1 to realize dry air required for a temperature environment of 15°C to -60°C. A control system 9 is arranged on one side of the engine to be tested. The control system 9 is composed of a computer. One ends of the refrigeration unit 2, the heat exchanger 10, and the vacuum pump unit 3 are respectively connected to a chiller 8 through a circulation pipe. After the gas then enters the tail gas treatment device 12 for purification treatment, it enters the second pressure stabilizing tank 11 for secondary pressure stabilization, and finally is pumped out by the vacuum pump unit 3. The vacuum pump unit 3 operates continuously to ensure that the entire system maintains within the environmental pressure range required by the set altitude. The deviation part is adjusted by the intake and exhaust proportional valve 4 to meet the pressure requirements of high-altitude simulation. Through the coordinated control of the intake and exhaust proportional valve 4 and the vacuum pump unit 3, accurate simulation with a pressure fluctuation range of ≤±1% and a temperature deviation of ≤±1°C at an altitude of 0 - 12000 meters is achieved, meeting the airworthiness certification standards.

[0019] Working principle: First, connect the external power supply. When the high-altitude simulation device is running, fresh air is provided through the fresh air system 1. These airs first flow through the intake and exhaust proportional valve 4, which precisely regulates the gas flow and pressure according to the working conditions of the engine to be tested. Then it enters the first pressure stabilizing tank 5, and the pressure fluctuations generated by the dynamic changes of the working conditions of the engine to be tested and during the air supply process are smoothed through the first pressure stabilizing tank 5 to ensure the stable air pressure delivered to the engine to be tested.

[0020] After the engine under test starts working, a part of the excess fresh air and the exhaust gas of the engine under test pass through the intake and exhaust proportional valve 4. The intake and exhaust proportional valve 4 also precisely regulates the gas flow rate and pressure so that the discharged gas can match the dynamic conditions of the engine under test and the pressure requirements at different altitudes. These gases then enter the exhaust gas treatment device 12 for purification, and then enter the second pressure stabilizing tank 11 for secondary pressure stabilization. Finally, they are pumped out by the vacuum pump unit 3. The vacuum pump unit 3 operates continuously to ensure that the entire system maintains within the environmental pressure range required at the set altitude. The deviation part is adjusted by the intake and exhaust proportional valve 4 to meet the pressure requirements for high-altitude simulation. During this process, the refrigeration unit 2 provides the cooling capacity required to produce low-temperature gas for the fresh air system 1 at three cooling capacity levels. Among them, the temperature deviation part is regulated by the pipeline heating device 7. The chilled water unit 8 provides cooling water for each device during operation. The entire operation process is monitored and adjusted by the control system 9 for the operation parameters of each module and the recording of process operation data. Through the coordinated cooperation of each component, the high-altitude simulation equipment can stably and efficiently simulate the high-altitude environment, providing a reliable guarantee for the performance test of the engine under test.

[0021] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than limiting the protection scope of the present invention. Any simple modification or equivalent replacement of the technical solution of the present invention by those of ordinary skill in the art does not depart from the essence and scope of the technical solution of the present invention.

Claims

1. A high-altitude environment simulation device for general aviation engines, comprising a fresh air system (1), a refrigeration unit (2), and the engine to be tested, characterized in that: The output end of the fresh air system (1) is installed with a connecting pipeline (6). On one side of the connecting pipeline (6), there is a refrigeration unit (2) connected to its interior. An intake and exhaust ratio valve (4) is arranged on the inner side wall of the connecting pipeline (6) close to the refrigeration unit (2). A pipeline heating device (7) is arranged on the outer wall of the connecting pipeline (6) close to the intake and exhaust ratio valve (4). On one side of the connecting pipeline (6) away from the pipeline heating device (7), there is a first pressure stabilizing tank (5), and the input end and the output end of the first pressure stabilizing tank (5) are respectively connected to the connecting pipeline (6) and one end of the engine to be measured. A vacuum pump unit (3) connected to its interior is arranged on one side of the connecting pipeline (6) through a check valve, and heat exchangers (10) are respectively arranged on both sides of the vacuum pump unit (3).

2. The aeroengine high altitude environment simulation device for general aviation according to claim 1, characterized in that: The fresh air system (1) consists of a dehumidifier and a pipeline.

3. A high-altitude environment simulation device for a general aviation engine according to claim 1, characterized in that: The refrigeration unit (2) consists of a compressor, a condenser, an evaporator and a pipeline.

4. A high-altitude environment simulation device for a general aviation engine according to claim 1, characterized in that: A tail gas treatment device (12) is arranged at the tail gas end of the engine to be measured through the connecting pipeline (6), and a second pressure stabilizing tank (11) connected to the vacuum pump unit (3) is installed at one end of the connecting pipeline (6) close to the tail gas treatment device (12).

5. A high-altitude environment simulation device for a general aviation engine according to claim 4, characterized in that: The tail gas treatment device (12) consists of a filter and a pipeline.

6. The aeroengine high altitude environment simulation device for general aviation according to claim 1, characterized in that: The refrigeration unit (2) provides cold energy for the fresh air system (1) to realize the dry air required for a temperature environment of 15°C to -60°C.

7. A high-altitude environment simulation device for a general aviation engine according to claim 1, characterized in that: A control system (9) is arranged on one side of the engine to be measured.

8. The aeroengine high altitude environment simulation device for general aviation according to claim 7, characterized in that: The control system (9) consists of a computer.

9. A high-altitude environment simulation device for a general aviation engine according to claim 1, characterized in that: One ends of the refrigeration unit (2), the heat exchanger (10) and the vacuum pump unit (3) are respectively connected to a chiller (8) through a circulation pipe.

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