A medium resistance performance test system and method for aircraft engine pipelines
By designing a test system for medium resistance performance of aero engine pipelines and simulating a variety of environmental parameters, the problem that the existing technology cannot comprehensively evaluate pipeline performance is solved, more efficient and stable tests are achieved, and economic benefits are improved.
Patent Information
- Application Number
- CN202411395507.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-08
- Publication Date
- 2024-12-10
- Estimated Expiration
- 2044-10-08
AI Technical Summary
The existing technology cannot comprehensively simulate multiple environments in aero engine pipelines, and cannot effectively screen out pipelines that meet the strict working conditions requirements, resulting in the inability to comprehensively evaluate the media resistance performance of aero engine pipelines.
A test system for medium resistance performance of aero engine pipelines is designed, including electronic control system, delivery device, working chamber, test pipeline, storage device, fuel oil source, temperature control oil source and gas source. Different environmental parameters are set (such as temperature and pressure) simulates high temperature and high pressure, high temperature and normal pressure, high temperature and low pressure, low temperature and other conditions, and uses valves and sensors to realize the automatic control and test process of the system.
Comprehensive performance tests of aircraft engine pipelines are achieved, the efficiency and stability of the test are improved, and the media resistance performance of the pipeline can be more comprehensively evaluated, which is more economical than traditional methods.
Smart Images
Figure CN118883079B_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a test system, and more particularly to a system and method for testing the medium resistance performance of an aircraft engine pipeline. Background Art
[0002] Aircraft engines operate under extremely demanding conditions. Typically, aircraft fly at altitudes between 0 and 12,000 meters, with some aircraft reaching altitudes exceeding 20,000 meters. Temperatures within the engine combustion chamber can reach 1,400°C to 2,700°C. Fluctuations in temperature and pressure can easily lead to deformation, oil leakage, and stress concentration in aircraft engine piping. Therefore, aircraft engine piping must exhibit strong resistance to high pressure, high temperature, and corrosion. Therefore, selecting aircraft engine piping that meets these operating conditions during the testing phase is crucial for aircraft engine development, delivery, and subsequent operation.
[0003] Aircraft engine piping media resistance testing can simulate the operating environment of aircraft engine piping and screen out engine piping that meets actual operating requirements. Currently, aircraft engine piping media resistance testing is still conducted using traditional methods, focusing solely on a specific environment. There is no comprehensive media resistance testing method, making it impossible to comprehensively simulate the various environments within aircraft engine piping and failing to meet development needs. Summary of the Invention
[0004] The purpose of the present invention is to provide a system and method for testing the medium resistance performance of aircraft engine pipelines in response to the problems existing in the prior art.
[0005] To achieve the above-mentioned purpose, the technical solution of the present invention is: an aircraft engine pipeline medium resistance performance test system, including an electronic control system, a delivery device, a working chamber, a test pipeline, a receiving device, a fuel oil source, a temperature control oil source and an air 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 through a connecting pipeline I, the fuel oil source is connected to the working chamber through the oil inlet pipeline I, the temperature control oil source is connected to the working chamber through the oil inlet pipeline II, and the air source is connected to the working chamber through the air transmission pipeline. The temperature-controlled oil source is connected to the connecting pipeline I through the connecting pipeline II, the working chamber is provided with an overflow port through the pipeline, the working chamber is provided with a pressure sensor, the oil inlet pipeline I is provided with a valve I, the oil inlet pipeline II is provided with a valve II and a temperature sensor II, the connecting pipeline II is provided with a valve III, the connecting pipeline I is provided with a valve V, the gas source is provided with a pressure regulating port, and the pipeline of the overflow port is provided with a valve IV. The 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 provided with a temperature sensor I, and the temperature sensor I is connected to the electronic control system.
[0007] A method for testing the medium resistance performance of an aircraft engine pipeline, comprising the following steps when conducting a normal temperature and high pressure test: an electronic control system sets the test system to an initial state, keeping valves I, II, III, IV, and V all closed; opening valves IV and III, allowing lubricating oil in a temperature-controlled oil source to flow into the test pipeline through valve III and out of an overflow port through valve IV, ensuring that no gas remains in the test pipeline; and closing valve IV; pressurizing the air source, monitoring the pressure in the working chamber and the test pipeline via a pressure sensor; when the pressure sensor reading reaches a set pressure of the electronic control system, the electronic control system starts an internal timer for 10 seconds; then closing the air source and opening valve V to discharge the lubricating oil in the test pipeline; opening valve I to verify whether the aviation kerosene passes smoothly through the test pipeline, and then releasing a rolling ball via a releasing device to verify whether it passes smoothly through the test pipeline, thereby verifying the medium resistance performance of the aircraft engine pipeline, thereby completing the normal temperature and high pressure performance test;
[0008] The high-temperature and normal-pressure test includes the following steps: the electronic control system sets the test system to the initial state, keeping valves I, II, III, IV, and V all closed; heating the temperature-controlled oil source, 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; valve II is then closed, and the temperature-controlled oil source is set to room temperature; valve I is opened to verify whether the aviation kerosene can pass through the test pipeline smoothly, and then a rolling ball is released through the release device to verify whether it can pass through the test pipeline smoothly, thereby verifying the medium resistance performance of the aircraft engine pipeline, thereby completing the high-temperature and normal-pressure performance test;
[0009] The following steps are included when conducting a high-temperature and high-pressure test: the electronic control system sets the test system to the initial state, and keeps valves I, II, III, IV, and V in the closed state; the temperature-controlled oil source is heated, and the 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; valve II is then closed, and the temperature of the temperature-controlled oil source is set to room temperature; the gas source is pressurized, and the pressure in the working chamber and the test pipeline is monitored by the 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; the gas source is then closed, and valve V is opened, and the lubricating oil in the test pipeline is discharged; valve I is opened to verify whether the aviation kerosene passes through the test pipeline smoothly, and then the rolling ball is released through the release device to verify whether it can pass through the test pipeline smoothly, thereby verifying the medium resistance performance of the aircraft engine pipeline, thereby 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 the initial state, and keeps valves I, II, III, IV, and V in the closed state; the temperature-controlled oil source is heated, and the 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; valve II is then closed, and the temperature of the temperature-controlled oil source is set to room temperature; valve V is opened, and the lubricating oil in the test pipeline is discharged; the air source is pumped out, and the pressure in the working chamber and the test pipeline is monitored by the 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; the air source is closed again; valve I is opened to verify whether the aviation kerosene passes through the test pipeline smoothly, and then the rolling ball is released through the release device to verify whether it can pass through the test pipeline smoothly, and then the medium resistance performance of the aircraft engine pipeline is verified, thereby completing the high-temperature and low-pressure performance test;
[0011] The normal temperature and low pressure test includes the following steps: the electronic control system sets the test system to the initial state, and keeps valves I, II, III, IV, and V in the closed state; the temperature of the temperature-controlled oil source is controlled, and the 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 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, and the lubricating oil in the test pipeline is discharged; the air source is pumped out, and the pressure in the working chamber and the test pipeline is monitored by the 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 the aviation kerosene can pass through the test pipeline smoothly, and then the rolling ball is released through the release device to verify whether it can pass through the test pipeline smoothly, and then the medium resistance performance of the aircraft engine pipeline is verified, thereby completing the normal temperature and low pressure performance test.
[0012] The present invention can simulate 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 environments in aircraft engine pipelines, thereby realizing comprehensive testing of the medium resistance performance of aircraft engine pipelines. Compared with traditional testing methods, the present invention is more efficient and stable and can achieve greater economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 This is a schematic diagram of the system structure.
[0014] Figure 2 This is a flow chart of the test method.
[0015] In the figure, valve I1, valve II2, valve III3, valve IV4, valve V5, delivery 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, connecting pipeline II21. DETAILED DESCRIPTION
[0016] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.
[0017] See also Figure 1-Figure 2 A system for testing the medium resistance of aircraft engine pipelines is provided. This system tests the performance of aircraft engine pipelines in resisting high-temperature, high-pressure, and other media. The system includes an electronic control system, a delivery device 6, a working chamber 7, a test pipeline 8, a storage device 9, a fuel source 10, a temperature-controlled oil source 13, and an air source 15. The storage device 9 may be a waste liquid tank, and the air source 15 may be an air pump. The delivery device 6 is connected to the working chamber 7, which is connected to the test pipeline 8. The test pipeline 8 is connected to the storage device 9 via a connecting pipeline I 20. The fuel source 10 is connected to the working chamber 7 via an oil inlet pipeline I 18. The temperature-controlled oil source 13 is connected to the working chamber 7 via an oil inlet pipeline II 19. The air source 15 is connected to the working chamber 7 via an air transmission pipeline 16. The temperature-controlled oil source 13 is connected to the connecting pipeline I 20 via a connecting pipeline II 21. The working chamber 7 is provided with an overflow port 11 through a pipeline. A pressure sensor 17 is provided on the working chamber 7. A valve I1 is provided on the oil inlet pipeline I 18. A valve II2 and a temperature sensor II 14 are provided on the oil inlet pipeline II 19. A valve III3 is provided on the connecting pipeline II 21. A valve V5 is provided on the connecting pipeline I 20. A valve IV4 is provided on the pipeline leading to the pipeline overflow port 11. A pressure regulating port is provided on the gas source 15. The valves I1, II2, III3, IV4, V5, temperature sensor II 14, and pressure sensor 17 are respectively connected to the electronic control system.
[0018] See also Figure 1-Figure 2 The temperature-controlled oil source 13 is provided with a temperature sensor Ⅰ 12 , and the temperature sensor Ⅰ 12 is connected to the electronic control system.
[0019] See also Figure 1-Figure 2In this test system, the engine medium resistance performance test part is mainly composed of the delivery device 6, the working chamber 7, the test pipeline 8 and the pressure sensor 17; the fuel source part is mainly composed of the fuel source 10, the valve I1 and the oil inlet pipeline I18; the temperature control oil source part is mainly composed of the temperature control oil source 13, the temperature sensor I12, the temperature sensor II14, the valve II2 and the oil inlet pipeline II19; the air pressure regulation part is mainly composed of the air source 15 and the air transmission pipeline 16; the waste liquid recovery part is mainly composed of the storage device 9 and the valve V5.
[0020] See also Figure 1-Figure 2 This test system uses kerosene as the test medium to pass through the aircraft engine pipeline, and 4016 lubricating oil is used to control the aircraft engine pipeline temperature. A fuel oil source 10, a temperature-controlled oil source 13, an air source 15, and an 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 oil source 13 and the air source 15. The test medium is recovered by the storage device 9, and the successful passage of the aviation kerosene through the test pipeline 8 is then verified. Finally, a ball is released using the release device 6 to test the medium resistance of the aircraft engine pipeline. The ball's function is to test the pipeline's passability, that is, its medium resistance. If the ball can pass through the working chamber 7, successfully pass through the test pipeline 8, and fall into the storage device 9, the test pipeline is determined to have passed the aircraft engine pipeline medium resistance test. If the ball fails to pass through the test pipeline 8, the test pipeline is determined to have failed the aircraft engine pipeline medium resistance test.
[0021] See also Figure 1-Figure 2 A method for testing the medium resistance performance of aircraft engine pipelines is applicable to the medium resistance performance test of aircraft engine pipelines. This method can simulate various environments in aircraft 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 normal temperature, 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 all closed; valves IV4 and III3 are opened, allowing 4106 lubricating oil from temperature-controlled oil source 13 to flow through valve III3 into test pipe 8 and out through valve IV4 from overflow port 11, ensuring that no gas remains in test pipe 8; valve IV4 is then closed; gas source 15 is pressurized, and the pressure in working chamber 7 is monitored via pressure sensor 17, thereby monitoring the pressure in test pipe 8 (at this point, the pressure in test pipe 8 can be considered equal to the pressure in working chamber 7). When the reading on pressure sensor 17 reaches the set pressure of the electronic control system, the electronic control system starts its internal timer for 10 seconds; gas source 15 is then closed, valve V5 is opened, and the 4016 lubricating oil in test pipe 8 is completely drained. Open valve Ⅰ1 to verify whether the aviation kerosene can pass through the test pipeline 8 smoothly, and then release the ball through the release device 6 to verify whether it can pass through the test pipeline 8 smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the normal temperature and high pressure performance test.
[0023] The high-temperature, normal-pressure test involves the following steps: the electronic control system sets the test system to its initial state, keeping valves I1, II2, III3, IV4, and V5 closed. Temperature-controlled oil source 13 is heated, and temperature sensor II 14 monitors the oil temperature. When the oil temperature reaches the electronic control system's set temperature, valves II2 and V5 are opened, allowing high-temperature 4016 lubricating oil to flow through test pipeline 8. The electronic control system then starts its internal timer for one minute. Valve II2 is then closed, and the electronic control system shuts down the temperature-controlled oil source's temperature control system. Valve I1 is opened to verify that the aviation kerosene flows smoothly through test pipeline 8. A rolling ball is then released through release device 6 to verify its smooth passage through test pipeline 8, thereby verifying the medium resistance of the aircraft engine pipeline, thus completing the high-temperature, normal-pressure performance test.
[0024] The following steps are involved in the high-temperature, high-pressure test: the electronic control system sets the test system to its initial state, keeping valves I1, II2, III3, IV4, and V5 closed. Temperature-controlled oil source 13 is heated, and temperature sensor II 14 monitors the oil temperature. When the oil temperature reaches the electronic control system's set temperature, valves II2 and V5 are opened, allowing the high-temperature lubricating oil to flow through test pipeline 8. The electronic control system then starts its internal timer for one minute. Valve II2 is then closed, and the temperature-controlled oil source is set to room temperature. Air source 15 is pressurized, and pressure sensor 17 monitors the pressure within working chamber 7 and test pipeline 8. When the pressure sensor 17 reaches the electronic control system's set pressure, the electronic control system starts its internal timer for 10 seconds. Air source 15 is then closed, and valve V5 is opened, draining the lubricating oil from test pipeline 8. Open valve Ⅰ1 to verify whether the aviation kerosene passes through the test pipeline 8 smoothly, and then release the ball through the release device 6 to verify whether it can pass through the test pipeline 8 smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the high temperature and high pressure performance test.
[0025] The high-temperature, 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 II 14 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 one minute. Valve II2 is then closed, and the temperature of the temperature-controlled oil source is set to room temperature. Valve V5 is opened, draining the lubricating oil from the test pipeline 8. Air source 15 is depressurized, and pressure sensor 17 monitors the pressure in the working chamber 7 and the test pipeline 8. When the pressure sensor 17 reaches the pressure set by the electronic control system, the electronic control system starts its internal timer for 10 seconds. Air source 15 is then closed. Open valve Ⅰ1 to verify whether the aviation kerosene can pass through the test pipeline 8 smoothly, and then release the ball through the release device 6 to verify whether it can pass through the test pipeline 8 smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the high temperature and low pressure performance test.
[0026] The normal temperature and low pressure test includes the following steps: the electronic control system sets the test system to the initial state, and keeps valves I1, II2, III3, IV4, and V5 in the closed state; the temperature of the temperature-controlled 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, and 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 discharged. The air source 15 is pumped out, and the pressure in the working chamber 7 and the test pipeline 8 is monitored through the pressure sensor 17. When the reading of the pressure sensor 17 reaches the set pressure of 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 the aviation kerosene passes through the test pipeline 8 smoothly, and then the rolling ball is released through the release device 6 to verify whether it can pass through the test pipeline 8 smoothly, and then the medium resistance performance of the aircraft engine pipeline is verified, thereby completing the normal temperature and low pressure performance test.
[0027] The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and the specific implementation of the present invention should not be considered to be limited to these descriptions. For those skilled in the art of the present invention, several simple deductions or substitutions can be made without departing from the concept of the present invention, and the above structures should be considered to fall within the scope of protection of the present invention.
Claims
1. A method for testing the medium resistance performance of an aircraft engine pipeline, wherein the aircraft engine pipeline medium resistance performance test system comprises an electronic control system, a delivery device (6), a working chamber (7), a test pipeline (8), a storage device (9), a fuel oil source (10), a temperature control oil source (13) and an air source (15), wherein the delivery device (6) is connected to the working chamber (7), the working chamber (7) is connected to the test pipeline (8), the test pipeline (8) is connected to the storage device (9) via a connecting pipeline I (20), the fuel oil source (10) is connected to the working chamber (7) via an oil inlet pipeline I (18), the temperature control oil source (13) is connected to the working chamber (7) via an oil inlet pipeline II (19), the air source (15) is connected to the working chamber (7) via an air supply pipeline (16), and the temperature control oil source (13) connected to the connecting pipeline I (20) through the connecting pipeline II (21), 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 gas source (15) is provided with a pressure regulating port, the pipeline of 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 electronic control system; It is characterized in that The following steps are included when conducting a normal temperature and high pressure test: The electronic control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4) and V (5) all in the closed state; opening valves IV (4) and III (3), allowing the lubricating oil in the temperature control oil source (13) to flow into the test pipeline (8) through valve III (3) and flow out from the overflow port (11) through valve IV (4), ensuring that there is no gas residue in the test pipeline (8), and then closing valve IV (4); The air 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 set pressure of the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source (15) is closed, and the valve V (5) is opened, and the lubricating oil in the test pipeline (8) is discharged; Open valve I (1) to verify whether the aviation kerosene can pass through the test pipeline (8) smoothly, then release the ball through the release device (6) to verify whether it can pass through the test pipeline (8) smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the normal temperature and high pressure performance test; The high temperature and normal pressure test includes the following steps: The electronic control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) all in the closed state; The temperature control 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 control oil source is set to normal temperature. Open valve I (1) to verify whether the aviation kerosene can pass through the test pipeline (8) smoothly, then release the ball through the release device (6) to verify whether it can pass through the test pipeline (8) smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the high temperature and normal pressure performance test; The following steps are included when conducting high temperature and high pressure tests: The electronic control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) all in the closed state; The temperature control 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 control oil source is set to normal temperature. The air 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 set pressure of the electronic control system, the electronic control system starts its internal timer for 10 seconds; then the air source (15) is closed, and the valve V (5) is opened, and the lubricating oil in the test pipeline (8) is discharged; Open valve I (1) to verify whether the aviation kerosene can pass through the test pipeline (8) smoothly, then release the ball through the release device (6) to verify whether it can pass through the test pipeline (8) smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the high temperature and high pressure performance test; The high temperature and low pressure test includes the following steps: The electronic control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) all in the closed state; The temperature control 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. Valve II (2) is then closed, and the temperature of the temperature control 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 depressurized, 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 set pressure of the electronic control system, the electronic control system starts its internal timer for 10 seconds, and then closes the gas source (15); Open valve I (1) to verify whether the aviation kerosene can pass through the test pipeline (8) smoothly, then release the ball through the release device (6) to verify whether it can pass through the test pipeline (8) smoothly, and then verify the medium resistance performance of the aircraft engine pipeline, thereby completing the high temperature and low pressure performance test; The normal temperature and low pressure test includes the following steps: The electronic control system sets the test system to the initial state, keeping valves I (1), II (2), III (3), IV (4), and V (5) all in the closed state; The temperature of the temperature-controlled oil source (13) is controlled, 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 normal 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. The lubricating oil in the test pipeline (8) is discharged. The gas source (15) is depressurized, 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 set pressure of the electronic control system, the electronic control system starts its internal timer for 10 seconds, and then closes the gas source (15); Open valve I (1) to verify whether the aviation kerosene can pass through the test pipeline (8) smoothly, and then release the ball through the release device (6) to verify whether it can pass through the test pipeline (8) smoothly, thereby verifying the medium resistance performance of the aircraft engine pipeline, thereby completing the normal temperature and low pressure performance test.
2. A method for testing the medium resistance performance of aircraft engine pipelines according to claim 1, Features: The temperature-controlled oil source (13) is provided with a temperature sensor I (12), and the temperature sensor I (12) is connected to the electronic control system.