Test system and method for medium-resistance performance of aero-engine piping

Abstract

A test system and method for medium-resistance performance of aero-engine piping. The test system comprises an electronic control system, a delivery device, a working cavity, test piping, a waste liquid tank / storage device, a fuel oil source, a temperature‑controlled oil source, and an air source / air pump; the delivery device is connected to the working cavity; the working cavity is connected to the test piping; the test piping is connected to the waste liquid tank / storage device; the fuel oil source is communicated with the working cavity; the temperature‑controlled oil source is communicated with the working cavity; the air source / air pump is connected to the working cavity; an overflow port is formed at the working cavity through a pipe; and a pressure sensor is provided on the working cavity. The test method is used for testing the medium-resistance performance of the aero-engine piping, which can simulate various environments such as high temperature and high pressure, high temperature and normal pressure, high temperature and low pressure, normal temperature and high pressure, and normal temperature and low pressure in the aero-engine piping, thereby comprehensively testing the medium-resistance performance of the aero-engine piping. Compared with conventional test methods, the test method is more efficient and stable, and can achieve greater economic benefits.

Description

A test system and method for testing the resistance of aero-engine piping to various media. Technical Field

[0001] This invention relates to a testing system, and more specifically to a testing system and method for the resistance of aero-engine piping to media. Background Technology

[0002] Aero-engines operate under extremely harsh conditions. Generally, aircraft fly at altitudes between 0m and 12,000m, with some reaching altitudes exceeding 20,000m. Temperatures within the engine combustion chamber can reach 1400℃ to 2700℃. Due to variations in temperature and pressure, aero-engine piping is highly susceptible to deformation, oil leaks, and stress concentration. Therefore, aero-engine piping requires strong resistance to high pressure, high temperatures, and corrosion. Consequently, selecting aero-engine piping that meets these operating conditions during the testing phase is crucial for aero-engine development, delivery, and subsequent use.

[0003] Media resistance testing of aero-engine piping can simulate the operating environment of aero-engine piping and screen out engine piping that meets the requirements of actual operating conditions. Currently, media resistance testing of aero-engine piping is still conducted in a traditional way, performing media resistance tests on piping in a single environment. There is no comprehensive media resistance testing method, which cannot comprehensively simulate the multiple environments within aero-engine piping and cannot meet development needs. Summary of the Invention

[0004] The purpose of this invention is to address the problems existing in the prior art by providing a test system and method for the resistance of aero-engine pipelines to media.

[0005] To achieve the above objectives, the technical solution of the present invention is: a test system for the media resistance performance of an aero-engine pipeline, comprising an electronic control system, a delivery device, a working chamber, a test pipeline, a receiving device, a fuel source, a temperature-controlled fuel source, and a gas source. The delivery device is connected to the working chamber, the working chamber is connected to the test pipeline, the test pipeline is connected to the receiving device via connecting pipeline I, the fuel source is connected to the working chamber via fuel inlet pipeline I, the temperature-controlled fuel source is connected to the working chamber via fuel inlet pipeline II, and the gas source is connected to the working chamber via a gas delivery pipeline. The temperature-controlled oil source is connected to the connecting pipe I via connecting pipe II. The working chamber is provided with an overflow port via a pipe. A pressure sensor is provided on the working chamber. Valve I is provided on the oil inlet pipe I. Valve II and temperature sensor II are provided on the oil inlet pipe II. Valve III is provided on the connecting pipe II. Valve V is provided on the connecting pipe I. A pressure regulating port is provided on the air source. Valve IV is provided on the overflow port pipe. Valve I, Valve II, Valve III, Valve IV, Valve V, temperature sensor II, and pressure sensor are respectively connected to the electronic control system.

[0006] The temperature-controlled oil source is equipped with a temperature sensor I, which is connected to the electronic control system.

[0007] A method for testing the media resistance performance of aero-engine pipelines includes the following steps during a normal temperature and high pressure test: The electronic control system sets the test system to its initial state, keeping valves I, II, III, IV, and V closed; valves IV and III are opened, allowing lubricating oil from the temperature-controlled oil source to flow into the test pipeline via valve III and out through the overflow port via valve IV, ensuring no gas residue remains in the test pipeline; valve IV is then closed; the gas source is pressurized, and the pressure in the working chamber and test pipeline is monitored by a pressure sensor. When the pressure sensor reading reaches the pressure set by the electronic control system, the system starts its internal timer for 10 seconds; the gas source is then closed, and valve V is opened, allowing the lubricating oil in the test pipeline to be completely discharged; valve I is opened to verify whether aviation kerosene can pass smoothly through the test pipeline, and then a ball is released via a dispensing device to verify whether it can pass smoothly through the test pipeline, thereby verifying the media resistance performance of the aero-engine pipeline and completing the normal temperature and high pressure performance test;

[0008] The high-temperature and atmospheric-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I, II, III, IV, and V closed; the temperature-controlled oil source is heated, and temperature sensor II monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II and V are opened to allow the high-temperature lubricating oil to pass through the test pipeline, and the electronic control system starts its internal timer for 1 minute; then valve II is closed, and the temperature-controlled oil source is set to room temperature; valve I is opened to verify whether aviation kerosene can pass smoothly through the test pipeline, and then a ball is released through the release device to verify whether it can pass smoothly through the test pipeline, thereby verifying the medium resistance performance of the aero-engine pipeline, thus completing the high-temperature and atmospheric-pressure performance test;

[0009] The high-temperature and high-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I, II, III, IV, and V closed; the temperature-controlled oil source is heated, and temperature sensor II monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II and V are opened to allow the high-temperature lubricating oil to pass through the test pipeline, and the electronic control system starts its internal timer for 1 minute; then valve II is closed, and the temperature of the temperature-controlled oil source is set to room temperature; the air source is pressurized, and the pressure in the working chamber and test pipeline is monitored by a pressure sensor. When the pressure sensor reading reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source is closed, and valve V is opened, and the lubricating oil in the test pipeline is discharged; valve I is opened to verify whether aviation kerosene can pass smoothly through the test pipeline, and then a ball is released through the release device to verify whether it can pass smoothly through the test pipeline, thereby verifying the medium resistance performance of the aero-engine pipeline, thus completing the high-temperature and high-pressure performance test;

[0010] The high-temperature and low-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I, II, III, IV, and V closed; the temperature-controlled oil source is heated, and temperature sensor II monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II and V are opened to allow the high-temperature lubricating oil to pass through the test pipeline, and the electronic control system starts its internal timer for 1 minute; then valve II is closed, and the temperature-controlled oil source temperature is set to room temperature; valve V is opened, and the lubricating oil in the test pipeline is completely discharged; the air source is pressurized, and the pressure in the working chamber and the test pipeline is monitored by a pressure sensor. When the pressure sensor reading reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source is closed; valve I is opened to verify whether aviation kerosene can pass smoothly through the test pipeline, and then a ball is released through the release device to verify whether it can pass smoothly through the test pipeline, thereby verifying the medium resistance performance of the aero-engine pipeline, thus completing the high-temperature and low-pressure performance test;

[0011] The following steps are included in the normal temperature and low pressure test: The electronic control system sets the test system to the initial state, keeping valves I, II, III, IV, and V closed; the temperature-controlled oil source is controlled, and temperature sensor II monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II and V are opened to allow normal temperature lubricating oil to pass through the test pipeline, and the electronic control system starts its internal timer for 1 minute; then valve II is closed; valve V is opened to drain the lubricating oil from the test pipeline; the air source is pressurized, and the pressure in the working chamber and test pipeline is monitored by a pressure sensor. When the pressure sensor reading reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source is closed; valve I is opened to verify whether aviation kerosene can pass smoothly through the test pipeline, and then a ball is released through the release device to verify whether it can pass smoothly through the test pipeline, thereby verifying the medium resistance performance of the aero-engine pipeline, thus completing the normal temperature and low pressure performance test.

[0012] This invention can simulate various environments within aero-engine piping, including high temperature and high pressure, high temperature and normal pressure, high temperature and low pressure, normal temperature and high pressure, and normal temperature and low pressure, enabling comprehensive testing of the medium resistance performance of aero-engine piping. Compared with traditional testing methods, it is more efficient and stable, and can achieve greater economic benefits. Attached Figure Description

[0013] Figure 1 is a schematic diagram of the system structure.

[0014] Figure 2 is a schematic diagram of the experimental method.

[0015] In the diagram, valve I1, valve II2, valve III3, valve IV4, valve V5, dispensing device 6, working chamber 7, test pipeline 8, receiving device 9, fuel oil source 10, overflow port 11, temperature sensor I12, temperature-controlled oil source 13, temperature sensor II14, gas source 15, gas pipeline 16, pressure sensor 17, oil inlet pipeline I18, oil inlet pipeline II19, connecting pipeline I20, and connecting pipeline II21. Detailed Implementation

[0016] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0017] Referring to Figures 1 and 2, a test system for the resistance of aero-engine pipelines to media is provided. This system tests the resistance of aero-engine pipelines to high-temperature and high-pressure media. It includes an electronic control system, a dispensing device 6, a working chamber 7, a test pipeline 8, a receiving device 9, a fuel source 10, a temperature-controlled fuel source 13, and a gas source 15. The receiving device 9 can be a waste liquid tank, and the gas source 15 can be an air pump. The dispensing device 6 is connected to the working chamber 7, which is connected to the test pipeline 8. The test pipeline 8 and the receiving device 9 are connected via connecting pipeline I 20. The fuel source 10 is connected to the working chamber 7 via fuel inlet pipeline I 18, and the temperature-controlled fuel source 13 is connected to the working chamber 7 via fuel inlet pipeline II 19. The gas source 15 is connected to the working chamber 7 via a gas delivery pipeline 16, and the temperature-controlled fuel source 13 is connected to connecting pipeline I 20 via connecting pipeline II 21. The working chamber 7 is equipped with an overflow port 11 via a pipeline. A pressure sensor 17 is installed on the working chamber 7. A valve 11 is installed on the oil inlet pipeline I 18. A valve 22 and a temperature sensor 214 are installed on the oil inlet pipeline II 19. A valve 3 is installed on the connecting pipeline II 21. A valve 5 is installed on the connecting pipeline I 20. A valve 4 is installed on the pipeline overflow port 11. A pressure regulating port is installed on the air source 15. Valves I 1, II 2, III 3, IV 4, V 5, temperature sensor II 14, and pressure sensor 17 are all connected to the electronic control system.

[0018] Referring to Figures 1 and 2, a temperature sensor I12 is installed on the temperature-controlled oil source 13, and the temperature sensor I12 is connected to the electronic control system.

[0019] Referring to Figures 1 and 2, the engine's resistance to media testing section mainly consists of the dispensing device 6, the working chamber 7, the test pipeline 8, and the pressure sensor 17; the fuel source section mainly consists of the fuel source 10, valve I1, and oil inlet pipeline I18; the temperature-controlled fuel source section mainly consists of the temperature-controlled fuel source 13, temperature sensor I12, temperature sensor II14, valve II2, and oil inlet pipeline II19; the air pressure regulation section mainly consists of the air source 15 and the air delivery pipeline 16; and the waste liquid recovery section mainly consists of the collection device 9 and valve V5.

[0020] Referring to Figures 1 and 2, this test system uses kerosene as the test medium through the aircraft engine pipeline, and controls the temperature of the aircraft engine pipeline using 4016 lubricating oil. The fuel source 10, temperature-controlled fuel source 13, air source 15, and overflow port 11 are connected to the working chamber 7. The air source 15 controls the pressure, and the test environment is controlled by the temperature-controlled fuel source 13 and the air source 15. The test medium is recovered through the collection device 9, and then the smooth passage of aviation kerosene through the test pipeline 8 is verified. Finally, a ball is launched using the launching device 6 to test the medium resistance performance of the aircraft engine pipeline. The ball's function is to test the pipeline's passability, i.e., its medium resistance performance. If the ball can pass smoothly through the working chamber 7 and through the test pipeline 8 into the collection device 9, the test pipeline has passed the aircraft engine pipeline medium resistance performance test; if the ball fails to pass through the test pipeline 8, the test pipeline has failed the aircraft engine pipeline medium resistance performance test.

[0021] Referring to Figures 1 and 2, a method for testing the resistance of aero-engine pipelines to media is described. This method can simulate various environments inside aero-engine pipelines, such as high temperature and high pressure, high temperature and normal pressure, high temperature and low pressure, normal temperature and high pressure, and normal temperature and low pressure.

[0022] The following steps are included in the normal temperature high pressure test: The electronic control system sets the test system to the initial state, keeping valves I1, II2, III3, IV4, and V5 closed; valves IV4 and III3 are opened, and the 4106 lubricating oil in the temperature-controlled oil source 13 flows into the test pipeline 8 through valve III3 and flows out through the overflow port 11 through valve IV4, ensuring that there is no gas residue in the test pipeline 8, and then valve IV4 is closed; the air source 15 is pressurized, and the pressure in the working chamber 7 is monitored by the pressure sensor 17, thereby realizing the monitoring of the pressure in the test pipeline 8 (at this time, the pressure in the test pipeline 8 can be considered equal to the pressure in the working chamber 7). When the reading of the pressure sensor 17 reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source 15 is closed, valve V5 is opened, and the 4016 lubricating oil in the test pipeline 8 is completely discharged. The valve I1 is opened to verify whether aviation kerosene can pass smoothly through the test pipeline 8. Then, a ball is released through the release device 6 to verify whether it can pass smoothly through the test pipeline 8, thereby verifying the performance of the aero-engine pipeline in resisting the medium, thus completing the normal temperature high pressure performance test.

[0023] The high-temperature and atmospheric-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I1, II2, III3, IV4, and V5 closed. The temperature-controlled oil source 13 is heated, and temperature sensor II14 monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II2 and V5 are opened, allowing high-temperature 4016 lubricating oil to flow through the test pipeline 8. The electronic control system starts its internal timer for 1 minute. Then, valve II2 is closed, and the electronic control system shuts down the temperature control system for the temperature-controlled oil source. Valve I1 is opened to verify whether aviation kerosene can smoothly pass through the test pipeline 8. A ball is then released via the dispensing device 6 to verify whether it can smoothly pass through the test pipeline 8, thereby verifying the medium resistance performance of the aero-engine pipeline and completing the high-temperature and atmospheric-pressure performance test.

[0024] The high-temperature and high-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I1, II2, III3, IV4, and V5 closed. The temperature-controlled oil source 13 is heated, and temperature sensor II14 monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II2 and V5 are opened, allowing the high-temperature lubricating oil to flow through the test pipeline 8. The electronic control system starts its internal timer for 1 minute. Then, valve II2 is closed, and the temperature of the temperature-controlled oil source is set to room temperature. The air source 15 is pressurized, and pressure sensor 17 monitors the pressure in the working chamber 7 and the test pipeline 8. When the reading of pressure sensor 17 reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds. Then, the air source 15 is closed, valve V5 is opened, and the lubricating oil in the test pipeline 8 is completely discharged. The valve I1 is opened to verify whether aviation kerosene can pass smoothly through the test pipeline 8. Then, a ball is released through the release device 6 to verify whether it can pass smoothly through the test pipeline 8, thereby verifying the medium resistance performance of the aero-engine pipeline and completing the high temperature and high pressure performance test.

[0025] The high-temperature and low-pressure test includes the following steps: The electronic control system sets the test system to its initial state, keeping valves I1, II2, III3, IV4, and V5 closed. The temperature-controlled oil source 13 is heated, and temperature sensor II14 monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II2 and V5 are opened, allowing the high-temperature lubricating oil to flow through the test pipeline 8. The electronic control system starts its internal timer for 1 minute. Then, valve II2 is closed, and the temperature-controlled oil source temperature is set to room temperature. Valve V5 is opened, and the lubricating oil in the test pipeline 8 is completely discharged. The air source 15 is pressurized, and the pressure in the working chamber 7 and the test pipeline 8 is monitored by pressure sensor 17. When the reading of pressure sensor 17 reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds. Then, the air source 15 is closed. The valve I1 is opened to verify whether aviation kerosene can pass smoothly through the test pipeline 8. Then, a ball is released through the release device 6 to verify whether it can pass smoothly through the test pipeline 8, thereby verifying the medium resistance performance of the aero-engine pipeline and completing the high temperature and low pressure performance test.

[0026] The following steps are included when conducting a normal temperature and low pressure test: The electronic control system sets the test system to the initial state, keeping valves I1, II2, III3, IV4, and V5 closed; the temperature control oil source 13 is controlled, and the temperature sensor II14 monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valves II2 and V5 are opened to allow the normal temperature lubricating oil to pass through the test pipeline 8. The electronic control system starts its internal timer for 1 minute; then valve II2 is closed; valve V5 is opened, and the lubricating oil in the test pipeline 8 is completely discharged. The gas source 15 is pressurized, and the pressure in the working chamber 7 and the test pipeline 8 is monitored by the pressure sensor 17. When the reading of the pressure sensor 17 reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds. Then the gas source 15 is shut off. Valve I1 is opened to verify whether aviation kerosene can pass smoothly through the test pipeline 8. Then the ball is released by the release device 6 to verify whether it can pass smoothly through the test pipeline 8, thereby verifying the medium resistance performance of the aero-engine pipeline, thus completing the normal temperature and low pressure performance test.

[0027] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, several simple deductions or substitutions can be made without departing from the concept of the present invention, and all such structures should be considered within the protection scope of the present invention.

Claims

1. A test system for the resistance of aero-engine piping to various media, characterized in that: The system includes an electronic control system, a dispensing device (6), a working chamber (7), a test pipeline (8), a receiving device (9), a fuel oil source (10), a temperature-controlled fuel oil source (13), and a gas source (15). The dispensing device (6) is connected to the working chamber (7), the working chamber (7) is connected to the test pipeline (8), the test pipeline (8) and the receiving device (9) are connected via connecting pipeline I (20), the fuel oil source (10) is connected to the working chamber (7) via oil inlet pipeline I (18), the temperature-controlled fuel oil source (13) is connected to the working chamber (7) via oil inlet pipeline II (19), the gas source (15) is connected to the working chamber (7) via gas supply pipeline (16), and the temperature-controlled fuel oil source (13) is connected to the connecting pipeline via connecting pipeline II (21). I (20) connection, the working chamber (7) is provided with an overflow port (11) through the pipeline, the working chamber (7) is provided with a pressure sensor (17), the oil inlet pipeline I (18) is provided with a valve I (1), the oil inlet pipeline II (19) is provided with a valve II (2) and a temperature sensor II (14), the connecting pipeline II (21) is provided with a valve III (3), the connecting pipeline I (20) is provided with a valve V (5), the air source (15) is provided with a pressure regulating port, the overflow port (11) is provided with a valve IV (4), the valve I (1), valve II (2), valve III (3), valve IV (4), valve V (5), temperature sensor II (14), and pressure sensor (17) are respectively connected to the electrical control system.

2. The test system for the resistance to media of aero-engine pipelines according to claim 1, characterized in that: The temperature-controlled oil source (13) is equipped with a temperature sensor I (12), which is connected to the electronic control system.

3. A method for testing the resistance of aero-engine piping to various media, characterized in that: The following steps are included when conducting a normal temperature high pressure test: The electrical control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) closed; valves IV (4) and III (3) are opened, and the lubricating oil in the temperature control oil source (13) flows into the test pipeline (8) through valve III (3) and flows out through the overflow port (11) through valve IV (4) to ensure that there is no gas residue in the test pipeline (8), and then valve IV (4) is closed; Pressurize the air source (15), monitor the pressure in the working chamber (7) and test pipeline (8) through the pressure sensor (17), and when the reading of the pressure sensor (17) reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then shut off the air source (15), open valve V (5), and the lubricating oil in the test pipeline (8) is discharged. Open valve I (1) to verify whether aviation kerosene can pass smoothly through the test pipeline (8), and then release the ball through the release device (6) to verify whether it can pass smoothly through the test pipeline (8), thereby verifying the performance of the aviation engine pipeline in resisting the medium, and thus completing the normal temperature high pressure performance test; The following steps are included when conducting a high-temperature, atmospheric-pressure test: The electrical control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) closed; The temperature-controlled oil source (13) is heated, and the temperature sensor II (14) monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valve II (2) and valve V (5) are opened to allow the high-temperature lubricating oil to pass through the test pipeline (8). The electronic control system starts its internal timer for 1 minute. Then valve II (2) is closed, and the temperature-controlled oil source is set to normal temperature. Open valve I (1) to verify whether aviation kerosene can pass smoothly through the test pipeline (8), and then release the ball through the release device (6) to verify whether it can pass smoothly through the test pipeline (8), thereby verifying the performance of the aviation engine pipeline against the medium, and thus completing the high temperature and normal pressure performance test. The following steps are included when conducting high temperature and high pressure tests: The electrical control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) closed; The temperature-controlled oil source (13) is heated, and the temperature sensor II (14) monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valve II (2) and valve V (5) are opened to allow the high-temperature lubricating oil to pass through the test pipeline (8). The electronic control system starts its internal timer for 1 minute. Then valve II (2) is closed, and the temperature of the temperature-controlled oil source is set to room temperature. Pressurize the air source (15), monitor the pressure in the working chamber (7) and test pipeline (8) through the pressure sensor (17), and when the reading of the pressure sensor (17) reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then shut off the air source (15), open valve V (5), and the lubricating oil in the test pipeline (8) is discharged. Open valve I (1) to verify whether aviation kerosene can pass smoothly through the test pipeline (8), and then release the ball through the release device (6) to verify whether it can pass smoothly through the test pipeline (8), thereby verifying the performance of the aviation engine pipeline in resisting the medium, and thus completing the high temperature and high pressure performance test; The following steps are included when conducting a high temperature and low pressure test: The electrical control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) closed; The temperature-controlled oil source (13) is heated, and the temperature sensor II (14) monitors the oil temperature. When the oil temperature reaches the temperature set by the electronic control system, valve II (2) and valve V (5) are opened to allow the high-temperature lubricating oil to pass through the test pipeline (8). The electronic control system starts its internal timer for 1 minute. Then valve II (2) is closed, and the temperature of the temperature-controlled oil source is set to room temperature. Valve V (5) is opened, and the lubricating oil in the test pipeline (8) is discharged. The gas source (15) is pressurized, and the pressure in the working chamber (7) and test pipeline (8) is monitored by the pressure sensor (17). When the reading of the pressure sensor (17) reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the gas source (15) is turned off. Open valve I (1) to verify whether aviation kerosene can pass smoothly through the test pipeline (8), and then release the ball through the release device (6) to verify whether it can pass smoothly through the test pipeline (8), thereby verifying the performance of the aviation engine pipeline in resisting the medium, and thus completing the high temperature and low pressure performance test. The following steps are included when conducting a room temperature low-pressure test: The electrical control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) closed; Temperature control is applied to the oil source (13). Temperature sensor II (14) monitors the oil temperature. When the oil temperature reaches the set temperature of the electronic control system, valve II (2) and valve V (5) are opened to allow room temperature lubricating oil to pass through the test pipeline (8). The electronic control system starts its internal timer for 1 minute. Then valve II (2) is closed and valve V (5) is opened to discharge the lubricating oil in the test pipeline (8). The gas source (15) is pressurized, and the pressure in the working chamber (7) and test pipeline (8) is monitored by the pressure sensor (17). When the reading of the pressure sensor (17) reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the gas source (15) is turned off. Open valve I (1) to verify whether aviation kerosene can pass smoothly through the test pipeline (8), and then release the ball through the release device (6) to verify whether it can pass smoothly through the test pipeline (8), thereby verifying the performance of the aviation engine pipeline in resisting the medium, and thus completing the normal temperature and low pressure performance test.

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