Aero-engine lubricating oil system oil supply and return matching test device and method

Abstract

The invention relates to the technical field of aero-engine lubricating oil system oil supply and return matching tests, and particularly discloses an aero-engine lubricating oil system oil supply and return matching test device and method. An aero-engine lubricating oil system oil supply and return matching test device comprises a lubricating oil storage piece, an oil outlet end and an oil inlet end of the lubricating oil storage piece are communicated with a lubricating oil pump set, and the lubricating oil pump set is communicated with a simulation bearing cavity; the gas supply equipment is communicated with the simulation bearing cavity; the environment chamber is arranged in a closed mode, the lubricating oil storage piece, the lubricating oil pump set and the simulation bearing cavity are all installed in the environment chamber, and the internal air pressure and the internal temperature of the environment chamber are suitable for being adjusted through adjusting equipment. The test device can simulate the conditions of different air pressures, different environment temperatures, air leakage of an engine bearing cavity sealing device and the like during operation of an aero-engine, the actual operation condition of oil supply and return matching of an aero-engine lubricating oil system can be reflected more truly, and the reliability and effectiveness of a test result are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of oil supply and return matching tests for aero-engine lubricating oil systems, and particularly relates to an oil supply and return matching test device and method for an aero-engine lubricating oil system. Background Art

[0002] The lubricating oil system is an important part of an aero-engine. The lubricating oil system generally includes an oil supply system and an oil return system. The oil supply system provides clean lubricating oil for the engine to lubricate and cool friction pairs such as bearings and gears. The oil return system pumps the lubricating and cooled lubricating oil back to the oil tank from each bearing cavity. The matching problem between the oil supply capacity and the oil return capacity of the lubricating oil system is the decisive factor for whether the lubricating oil system can work properly and better. When designing the lubricating oil system, the determination of the oil return capacity and the oil supply capacity of each bearing cavity of the engine often relies on experience and there is not much theoretical basis. After the lubricating oil system is designed, technicians formulate an oil supply and return matching test plan based on the designed lubricating oil system plan and complete the oil supply and return matching test to verify the feasibility of the design plan.

[0003] In the existing oil supply and return matching test for the lubricating oil system, the test atmospheric conditions are standard atmospheric conditions, and the influence of high-altitude conditions on the lubricating oil system is not considered. However, in the actual operating conditions of an aero-engine, situations such as a decrease in oil supply capacity caused by low air pressure and an increase in the flow resistance of the lubricating oil pipeline caused by low temperature conditions often occur, resulting in a large deviation between the test conditions of the existing oil supply and return matching test for the lubricating oil system and the actual operating conditions of the aero-engine, which affects the effectiveness of the test results. Summary of the Invention

[0004] In view of this, the present invention provides an oil supply and return matching test device and method for an aero-engine lubricating oil system to solve the problem of a large deviation between the test conditions in the existing oil supply and return matching test for the lubricating oil system and the actual operating conditions of the aero-engine.

[0005] In a first aspect, the present invention provides an oil supply and return matching test device for an aero-engine lubricating oil system, including:

[0006] A lubricating oil storage member, both its oil outlet end and oil inlet end are connected to an oil pump group. The oil pump group is connected to a simulated bearing cavity. The inlet end of the simulated bearing cavity is connected to the oil outlet end of the lubricating oil storage member through the oil pump group, and the outlet end of the simulated bearing cavity is connected to the oil inlet end of the lubricating oil storage member through the oil pump group;

[0007] An air supply device, connected to the simulated bearing cavity;

[0008] An environmental chamber, which is enclosed, and the lubricating oil storage member, the lubricating oil pump group and the simulated bearing cavity are all installed inside the environmental chamber, and the internal air pressure and internal temperature of the environmental chamber are suitable for being adjusted by adjusting equipment.

[0009] The aviation engine lubricating oil system supply and return oil matching test device stores lubricating oil through a lubricating oil storage member, and conveys the lubricating oil to the simulated bearing cavity by means of a lubricating oil pump group. The lubricating oil used in the simulated bearing cavity is then pumped back to the lubricating oil storage member by the lubricating oil pump group. The gas supply device supplies gas to the simulated bearing cavity to simulate the air leakage condition of the engine bearing cavity sealing device. At the same time, the internal air pressure and internal temperature of the environmental chamber can be adjusted by the adjusting equipment, so as to simulate the environmental conditions when the aviation engine operates at different altitudes and different environmental temperatures, so as to be able to carry out test verification on the supply and return oil matching of the aviation engine lubricating oil system, so as to determine whether the supply and return oil capabilities are matched and coordinated. The aviation engine lubricating oil system supply and return oil matching test device provided by the present invention can simulate various working conditions faced during the actual operation of the aviation engine, including the air pressure under different high-altitude environments, different environmental temperatures, air leakage of the engine bearing cavity sealing device, etc., and fully considers various factors that may affect the supply and return oil matching of the lubricating oil system during actual operation. Compared with the existing tests based only on the laboratory standard atmospheric conditions, the aviation engine lubricating oil system supply and return oil matching test device provided by the present invention can provide more comprehensive test conditions, can more truly reflect the actual operation status of the supply and return oil matching of the aviation engine lubricating oil system, and thus effectively improve the reliability and effectiveness of the test results, providing more accurate and powerful support for the design optimization and performance evaluation of the aviation engine lubricating oil system.

[0010] In an optional implementation manner, an oil-gas separation device is further included, the inlet end of which is communicated with the simulated bearing cavity, and the liquid side output end of which is communicated with the lubricating oil storage member.

[0011] During the operation of the device, the oil mist generated in the simulated bearing cavity enters the oil-gas separation device through the inlet end of the oil-gas separation device. The oil-gas separation device separates the oil mist into gas and liquid lubricating oil. The gas is discharged from the gas side of the oil-gas separation device, and the liquid lubricating oil flows into the lubricating oil storage member from the liquid side output end. In this way, the lubricating oil can be recycled, and at the same time, it can avoid the accumulation of oil mist in the simulated bearing cavity, which poses a safety hazard to the simulated bearing cavity.

[0012] In an optional implementation manner, an oil mist branch is communicated between the inlet end of the oil-gas separation device and the lubricating oil storage member.

[0013] During the operation of the device, by guiding the lubricating oil mist generated in the lubricating oil storage part to the oil-gas separation device for gas-liquid separation, the gas in the lubricating oil mist is discharged from the gas side of the oil-gas separation device, and the liquid flows back to the lubricating oil storage part, thereby realizing the treatment of the lubricating oil mist in the lubricating oil storage part and avoiding the impact of the lubricating oil mist on the safety performance of the lubricating oil storage part.

[0014] In an optional embodiment, the lubricating oil pump group includes a supply oil pump and a return oil pump. The supply oil pump is installed between the inlet end of the simulated bearing cavity and the outlet end of the lubricating oil storage part for transporting the lubricating oil in the lubricating oil storage part to the simulated bearing cavity; the return oil pump is installed between the outlet end of the simulated bearing cavity and the inlet end of the lubricating oil storage part for pumping back the lubricating oil used in the simulated bearing cavity to the lubricating oil storage part. Through the coordinated action of the supply oil pump and the return oil pump, the circulating flow of the lubricating oil between the lubricating oil storage part and the simulated bearing cavity is realized, ensuring that the lubricating oil can be continuously and stably supplied to the simulated bearing cavity for lubrication and cooling, and at the same time ensuring that the used lubricating oil can flow back to the lubricating oil storage part in time, maintaining the lubricating oil balance and normal operation of the system.

[0015] In an optional embodiment, at least two groups of the simulated bearing cavities are installed in parallel, and the return oil pumps are arranged in one-to-one correspondence with the simulated bearing cavities.

[0016] Each group of simulated bearing cavities can simultaneously simulate the working states of multiple engine bearing cavities. The return oil pump corresponding to each simulated bearing cavity can specifically suck the lubricating oil in the simulated bearing cavity and transport it back to the lubricating oil storage part, thereby realizing the synchronous test verification of the oil supply and return matching conditions of multiple bearing cavities. By simulating the oil supply and return collaborative working scenarios of multiple bearing cavities in a real engine, the comprehensiveness and authenticity of the test are improved, providing more detailed data support for the design optimization and performance evaluation of the multi-chamber lubricating oil system, and helping to improve the overall performance and reliability of the aero-engine lubricating oil system.

[0017] In an optional embodiment, a lubricating oil heater is installed on the pipeline between the inlet end of the simulated bearing cavity and the lubricating oil pump group.

[0018] The lubricating oil heater can heat the lubricating oil transported by the lubricating oil pump group to the simulated bearing cavity, adjust the temperature of the lubricating oil to reach the set test temperature value, thereby simulating the change of the lubricating oil viscosity of the aero-engine under different working temperature conditions, more truly reflecting the lubrication and flow characteristics of the lubricating oil in actual operation, helping to accurately evaluate the oil supply and return matching performance of the lubricating oil system under different temperature conditions, providing an important basis for the thermal management design and optimization of the lubricating oil system, and improving the applicability and accuracy of the test results.

[0019] In an alternative embodiment, a pressure regulating device is installed on the pipeline between the inlet end of the simulated bearing chamber and the lubricating oil pump set.

[0020] The pressure regulating device can adjust the lubricating oil pressure delivered by the lubricating oil pump set to the simulated bearing chamber to reach a set pressure value, thereby controlling the oil supply pressure, simulating the pressure change of the lubricating oil supply under different working conditions, ensuring that the lubricating oil can enter the simulated bearing chamber at an appropriate pressure to meet its lubrication requirements. It helps to deeply study the influence of the oil supply pressure on the oil supply and return oil matching of the lubricating oil system, provides strong support for the pressure regulation design and optimization of the lubricating oil system, and further improves the refinement degree of the test and the reliability of the results.

[0021] In an alternative embodiment, a pressure regulating device is installed on the pipeline between the lubricating oil pump set and the inlet end of the lubricating oil storage member.

[0022] The pressure regulating device can adjust the lubricating oil pressure delivered by the oil return pump to the lubricating oil storage member to stabilize it within the set oil return pressure range, thereby optimizing the oil return process, avoiding problems such as unsmooth oil return or impact on the lubricating oil storage member due to too high or too low oil return pressure, ensuring that the lubricating oil can return to the lubricating oil storage member smoothly and steadily, maintaining the lubricating oil circulation balance of the system, providing a reliable guarantee for the stable operation of the entire lubricating oil system, and improving the accuracy and repeatability of the test.

[0023] In an alternative embodiment, a driving device is installed at the driving end of the lubricating oil pump set, and the lubricating oil pump set is drivingly connected to the driving device through a test tooling.

[0024] The driving device drives the lubricating oil pump set to rotate through the test tooling, providing power support for the lubricating oil pump set. The lubricating oil pump set performs the operations of lubricating oil delivery and back pumping according to the set rotational speed requirements to ensure the circulating flow of the lubricating oil in the system. By adjusting the rotational speed of the lubricating oil pump set, the operating state of the lubricating oil pump under different working conditions is simulated, facilitating the study of the influence of the rotational speed of the lubricating oil pump on the oil supply and return oil matching of the lubricating oil system, further expanding the functions and application scope of the test device, and enhancing the flexibility and diversity of the test.

[0025] In a second aspect, the present invention also provides a method for testing the oil supply and return oil matching of an aeroengine lubricating oil system, which uses the aeroengine lubricating oil system oil supply and return oil matching test system of the present invention, and includes the following steps:

[0026] Control the internal pressure of the environmental chamber to atmospheric pressure and the internal temperature to the ambient temperature, and control the rotational speed value of the lubricating oil pump set to the set rotational speed so that the lubricating oil in the lubricating oil storage member is delivered to the simulated bearing chamber;

[0027] Close the lubricating oil pump set and record the lubricating oil level in the lubricating oil storage member;

[0028] Control the internal pressure of the environmental chamber to the set pressure and the internal temperature to the set temperature. Then, control the rotational speed of the lubricating oil pump set to the set rotational speed again, and start the gas supply equipment to introduce gas with a set flow rate into the simulated bearing cavity.

[0029] Observe and record the oil accumulation situation in the simulated bearing cavity.

[0030] By controlling the internal pressure and temperature of the environmental chamber, simulate the operating conditions of an aero-engine under different altitudes and temperature environments. Control the rotational speed of the lubricating oil pump set to regulate the delivery and return of lubricating oil. At the same time, start the gas supply equipment to simulate the air leakage conditions of the engine bearing cavity sealing device, making the test closer to the actual operating state of the aero-engine, being able to more truly reflect the actual operating conditions of the lubricating oil system's supply and return oil matching, and eliminating the influence of the difference between the standard test chamber conditions and the actual operating environment on the test results. By observing and recording the oil accumulation situation in the simulated bearing cavity, the supply and return oil matching ability of the lubricating oil system can be more accurately evaluated, providing more accurate data support for the design optimization and performance evaluation of the aero-engine lubricating oil system, and effectively improving the credibility and reliability of the test results. Description of the Drawings

[0031] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0032] Figure 1 It is a schematic structural diagram of the supply and return oil matching test device for the aero-engine lubricating oil system provided by the embodiment of the present invention.

[0033] Description of the reference numerals: 1. Environmental chamber; 2. Lubricating oil storage component; 3. Bearing simulation cavity; 4. Pressure regulating equipment; 5. Driving equipment; 6. Lubricating oil pump set; 61. Supply oil pump; 62. Return oil pump; 7. Oil-gas separation equipment; 8. Lubricating oil heater; 9. Test tooling; 10. Gas supply equipment; 11. Temperature sensor; 12. Flowmeter; 13. Pressure sensor. Detailed Embodiments

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0035] The following is combined with Figure 1 to describe embodiments of the present invention.

[0036] According to an embodiment of the present invention, on the one hand, an oil supply and return matching test device for an aeroengine lubricating oil system is provided, which includes an oil storage member 2, a gas supply device 10, and an environmental chamber 1.

[0037] Both the oil outlet end and the oil inlet end of the oil tank serving as the oil storage member 2 are connected to the oil pump group 6, and the oil pump group 6 is connected to the simulated bearing cavity. Specifically, the inlet end of the simulated bearing cavity is connected to the oil outlet end of the oil storage member 2 through the oil pump group 6, and the outlet end of the simulated bearing cavity is connected to the oil inlet end of the oil storage member 2 through the oil pump group 6. The gas supply device 10 is connected to the simulated bearing cavity and is used to introduce sealing air into the simulated bearing cavity to simulate the air leakage condition of the engine bearing cavity sealing device during actual operation. The environmental chamber 1 is a closable chamber, and the oil storage member 2, the oil pump group 6, and the simulated bearing cavity are all installed inside the environmental chamber 1. The gas supply device 10 is arranged outside the environmental chamber 1 and supplies gas to the simulated bearing cavity inside the environmental chamber 1 through a pipeline. The internal air pressure and internal temperature of the environmental chamber 1 can be adjusted through corresponding adjusting devices, so as to simulate the environmental conditions when the aeroengine operates at different altitudes and different environmental temperatures.

[0038] When the oil supply and return matching test device for the aeroengine lubricating oil system is working, first, the oil storage member 2 is used to store lubricating oil. During the test, the oil pump group 6 extracts the lubricating oil from the oil storage member 2 and transports it to the simulated bearing cavity. After the lubricating oil completes related operations such as lubrication in the simulated bearing cavity, it is then extracted by the oil pump group 6 and flows back to the oil storage member 2, forming a circulating oil supply and return system. At the same time, the gas supply device 10 introduces sealing air into the simulated bearing cavity to simulate the possible air leakage situation of the engine bearing cavity sealing device during actual operation. In addition, the internal air pressure and internal temperature of the environmental chamber 1 are adjusted through the adjusting device, so as to simulate the working conditions when the aeroengine operates in various different high-altitude environments and different temperature conditions.

[0039] The oil supply and return matching test device for an aero-engine lubricating oil system provided in this embodiment can simulate various working conditions faced during the actual operation of an aero-engine, covering various complex situations such as air pressure changes under different high-altitude environments, the influence of different ambient temperatures, and air leakage of the engine bearing cavity sealing device. Compared with the existing test devices that are only based on the standard atmospheric conditions in the laboratory, the test device has significant advantages in terms of the comprehensiveness of test conditions and can more truly reflect the status of the oil supply and return matching of the aero-engine lubricating oil system during actual operation. This can not only effectively improve the reliability and accuracy of test results, but also provide more comprehensive, accurate, and powerful data support for the design optimization and performance evaluation of the aero-engine lubricating oil system, contributing to the development and progress of related technologies for the aero-engine lubricating oil system and ensuring the stable operation and performance improvement of the aero-engine.

[0040] In one embodiment, an oil-gas separation device 7 is further included. The inlet end of the oil-gas separation device 7 is connected to the simulated bearing cavity, and the liquid-side output end is connected to the lubricating oil storage member 2. The oil-gas separation device 7 is installed outside the environmental chamber 1 so that the gas-side output end of the oil-gas separation device 7 is directly connected to the atmosphere.

[0041] During the operation of the device, the oil mist generated in the simulated bearing cavity enters the oil-gas separation device 7 through the inlet end of the oil-gas separation device 7. The oil-gas separation device 7 separates the oil mist into two parts: gas and liquid lubricating oil. The gas part is discharged from the gas side of the oil-gas separation device 7, and the liquid lubricating oil flows into the lubricating oil storage member 2 from the liquid-side output end, forming a cycle process to achieve the effective recycling of lubricating oil, and at the same time, it can also avoid potential safety hazards that may be caused by the accumulation of lubricating oil mist in the simulated bearing cavity.

[0042] Furthermore, an oil mist branch is connected between the inlet end of the oil-gas separation device 7 and the lubricating oil storage member 2.

[0043] During the operation of the device, by guiding the lubricating oil mist generated in the lubricating oil storage member 2 into the oil-gas separation device 7 for gas-liquid separation, the gas in the lubricating oil mist is discharged from the gas side of the oil-gas separation device 7, and the liquid flows back into the lubricating oil storage member 2, thereby realizing the treatment of the lubricating oil mist in the lubricating oil storage member 2 and avoiding the impact of the lubricating oil mist on the safety performance of the lubricating oil storage member 2.

[0044] In some other embodiments, two sets of oil-gas separation devices 7 are provided. One set of oil-gas separation devices 7 is installed between the simulated bearing cavity and the lubricating oil storage member 2, and the inlets and liquid-side outlets of the other set of oil-gas separation devices 7 are both connected to the lubricating oil storage member 2.

[0045] In this embodiment, the lubricating oil pump group 6 includes a supply oil pump 61 and a return oil pump 62. The supply oil pump 61 is installed between the inlet end of the simulated bearing cavity and the oil outlet end of the lubricating oil storage member 2, and is used to transport the lubricating oil in the lubricating oil storage member 2 to the simulated bearing cavity. The return oil pump 62 is installed between the outlet end of the simulated bearing cavity and the oil inlet end of the lubricating oil storage member 2, and is used to pump back the lubricating oil used in the simulated bearing cavity to the lubricating oil storage member 2. Through the coordinated action of the supply oil pump 61 and the return oil pump 62, the cyclic flow of the lubricating oil between the lubricating oil storage member 2 and the simulated bearing cavity is realized, ensuring that the lubricating oil can be continuously and stably supplied to the simulated bearing cavity for lubrication and cooling, and at the same time ensuring that the used lubricating oil can flow back to the lubricating oil storage member 2 in time, maintaining the lubricating oil balance and normal operation of the system.

[0046] Further, at least two groups of simulated bearing cavities are installed in parallel, and the return oil pump 62 is arranged in one-to-one correspondence with the simulated bearing cavities. In this embodiment, two groups of simulated bearing cavities are installed in parallel, and two groups of return oil pumps 62 are also installed in parallel within the lubricating oil pump group 6.

[0047] Each group of simulated bearing cavities can simultaneously simulate the working states of multiple engine bearing cavities. The return oil pump 62 corresponding to each simulated bearing cavity can specifically suck the lubricating oil in the simulated bearing cavity and transport it back to the lubricating oil storage member 2, thereby realizing the synchronous test verification of the oil supply and return matching conditions of multiple bearing cavities. By simulating the oil supply and return coordinated working scenarios of multiple bearing cavities in a real engine, the comprehensiveness and authenticity of the test are improved, providing more detailed data support for the design optimization and performance evaluation of the multi-chamber lubricating oil system, and helping to improve the overall performance and reliability of the aeroengine lubricating oil system.

[0048] In another alternative embodiment, the number of simulated bearing cavities can be expanded according to actual test requirements, for example, increased to three groups or more groups to simulate more complex engine bearing cavity layouts and working conditions. In yet another alternative embodiment, each simulated bearing cavity can be designed with different structures or sizes to simulate different types or specifications of engine bearing cavities, thereby improving the versatility and adaptability of the test device.

[0049] In this embodiment, an oil heater 8 is installed on the pipeline between the inlet end of the simulated bearing cavity and the lubricating oil pump group 6, and a pressure regulating valve serving as a pressure regulating device 4 is installed on the pipeline between the inlet end of the simulated bearing cavity and the lubricating oil pump group 6.

[0050] The lubricating oil heater 8 can heat the lubricating oil delivered by the lubricating oil pump group 6 to the simulated bearing cavity, adjust the temperature of the lubricating oil to reach the set test temperature value, so as to simulate the change of lubricating oil viscosity of the aero-engine under different working temperature conditions, more truly reflect the lubrication and flow characteristics of the lubricating oil during actual operation, help to accurately evaluate the oil supply and return matching performance of the lubricating oil system under different temperature conditions, provide an important basis for the thermal management design and optimization of the lubricating oil system, and improve the applicability and accuracy of the test results.

[0051] The pressure regulating device 4 can adjust the pressure of the lubricating oil delivered by the lubricating oil pump group 6 to the simulated bearing cavity to reach the set pressure value, so as to control the oil supply pressure, simulate the pressure change of lubricating oil supply under different working conditions, ensure that the lubricating oil can enter the simulated bearing cavity at an appropriate pressure to meet its lubrication requirements. It helps to deeply study the influence of the oil supply pressure on the oil supply and return matching of the lubricating oil system, provides strong support for the pressure regulation design and optimization of the lubricating oil system, and further improves the refinement degree of the test and the reliability of the results.

[0052] Specifically, a lubricating oil heater 8, a temperature sensor 11, a flowmeter 12, a pressure regulating valve and a pressure sensor 13 are successively installed on the pipeline at the output end of the lubricating oil pump group 6. A flowmeter 12 and a pressure regulating valve as the pressure regulating device 4 are respectively installed on the pipeline at the inlet end of each group of simulated bearing cavities.

[0053] In one embodiment, a pressure regulating device 4 is installed on the pipeline between the driving end of the lubricating oil pump group 6 and the oil inlet end of the lubricating oil storage part 2. The pressure regulating device 4 can adjust the pressure of the lubricating oil delivered by the oil return pump 62 to the lubricating oil storage part 2 to stabilize it within the set oil return pressure range, so as to optimize the oil return process, avoid problems such as unsmooth oil return or impact on the lubricating oil storage part 2 caused by too high or too low oil return pressure, ensure that the lubricating oil can return to the lubricating oil storage part 2 smoothly and stably, maintain the lubricating oil circulation balance of the system, provide a reliable guarantee for the stable operation of the entire lubricating oil system, and improve the accuracy and repeatability of the test.

[0054] Specifically, a flowmeter 12 is installed on the pipeline between the oil supply pump 61 and the lubricating oil storage part 2, and a flowmeter 12 and a pressure regulating valve as the pressure regulating device 4 are installed on the pipeline between the oil return pump 62 and the lubricating oil storage part 2.

[0055] In one embodiment, a driving motor as the driving device 5 is installed at the driving end of the lubricating oil pump group 6, and the lubricating oil pump group 6 and the driving device 5 are drivingly connected through a test tooling 9. The driving motor is installed outside the environmental chamber 1, and its output shaft penetrates through the side wall of the environmental chamber 1 and extends into the environmental chamber 1, and the output shaft of the driving motor is rotationally and sealingly fitted with the side wall of the environmental chamber 1.

[0056] The driving device 5 drives the oil pump group 6 to rotate through the test fixture 9, providing power support for the oil pump group 6. The oil pump group 6 performs the oil delivery and oil withdrawal operations according to the set speed requirements to ensure the circulation of the oil in the system. By adjusting the speed of the oil pump group 6, the operating state of the oil pump under different working conditions is simulated, which provides convenience for studying the influence of the oil pump speed on the oil supply and return matching of the oil system, further expands the function and application scope of the test device, and improves the flexibility and diversity of the test.

[0057] In summary, the aircraft engine lubricating oil system supply and return oil matching test device provided in this embodiment installs the aircraft engine lubricating oil pump group 6 on the test fixture 9, and the test fixture 9 is used to connect the lubricating oil pump group 6 and the drive motor, and the lubricating oil pump group 6 is driven to rotate by the drive motor. The lubricating oil pump group 6 consists of an oil supply pump 61 and two groups of return oil pumps 62 and return oil pumps 62. During the test, the oil supply pump 61 transports the lubricating oil in the lubricating oil tank of the aircraft engine to two groups of simulated bearing cavities, and the two groups of return oil pumps 62 respectively withdraw the lubricating oil in the two groups of simulated bearing cavities, and the withdrawn lubricating oil is aggregated and transported to the lubricating oil tank as the lubricating oil storage part 2. The test device is also provided with an air supply device 10 for providing sealing air, which is used to provide sealing air to the two groups of simulated bearing cavities, and is used to simulate the air leakage conditions of the engine bearing cavity sealing device. In this embodiment, the air supply device 10 uses an air storage tank. The test device is also provided with an oil-gas separation device 7, which is used to separate the oil mist generated in the lubricating oil box and the simulated bearing cavity during the test, and the air is discharged after separation, and the separated lubricating oil returns to the lubricating oil box. Furthermore, the test device is also provided with a pressure regulating valve, which is used to adjust the outlet pipeline pressure of the oil supply pump 61, the simulated bearing cavity oil supply flow, and the outlet pipeline pressure of the return oil pump 62. A temperature sensor 11 is provided to measure the outlet lubricating oil temperature of the oil supply pump 61. A flow meter 12 is provided to measure the outlet lubricating oil flow of the increased oil supply pump 61, the simulated bearing cavity oil supply flow, and the simulated bearing cavity sealing air flow. A pressure sensor 13 is provided to measure the inlet pipeline pressure of the oil supply pump 61, the outlet pipeline pressure of the pressure regulating valve, the inlet pipeline pressure of the return oil pump 62, and the outlet pipeline pressure of the return oil pump 62. The test device is provided with a lubricating oil heater 8, which is used to heat the outlet lubricating oil of the oil supply pump 61. An environmental chamber 1 is provided in the test device, and the pressure and temperature inside the chamber are adjustable, so as to provide working conditions of different altitudes and different ambient temperatures to the test pieces such as the lubricating oil tank, the lubricating oil pump group 6, and the simulated bearing cavity.

[0058] According to an embodiment of the present invention, on the other hand, a method for testing the oil supply and return oil matching of an aircraft engine lubricating oil system is provided. The method for testing the oil supply and return oil matching of an aircraft engine lubricating oil system of the present invention comprises the following steps:

[0059] Control the internal pressure of the environmental chamber 1 to atmospheric pressure and the internal temperature to ambient temperature. Control the rotational speed of the lubricating oil pump group 6 to the set rotational speed so that the lubricating oil in the lubricating oil storage part 2 is delivered to the simulated bearing cavity. Then, turn off the lubricating oil pump group 6 and record the lubricating oil level in the lubricating oil storage part 2.

[0060] Next, control the internal pressure of the environmental chamber 1 to the set pressure and the internal temperature to the set temperature. Again, control the rotational speed of the lubricating oil pump group 6 to the set rotational speed and start the gas supply device 10 to introduce a set flow rate of gas into the simulated bearing cavity. Observe and record the oil accumulation situation in the simulated bearing cavity.

[0061] Specifically, before the test, connect each test device to the inside of the environmental chamber 1 and add lubricating oil to the lubricating oil tank.

[0062] Start the drive motor, adjust the rotational speeds of the oil supply pump 61 and the oil return pump 62 to the set rotational speeds, start the lubricating oil heater 8, and heat the lubricating oil temperature at the outlet of the oil supply pump 61 to the set value. Adjust the four pressure regulating valves respectively so that the outlet pressure of the pressure regulating valve reaches the set pressure value, the lubricating oil supply flow rates of the two groups of simulated bearing cavities reach the set ratio, and the outlet pressure of the oil return pump 62 reaches the set pressure value. Turn off the drive motor, reduce the rotational speeds of the oil supply pump 61 and the oil return pump 62 to zero, turn off the lubricating oil heater 8, confirm the lubricating oil level in the lubricating oil tank, and close the door of the environmental chamber 1 to seal the environmental chamber 1.

[0063] Adjust the pressure inside the environmental chamber 1 to the set value and adjust the ambient temperature inside the environmental chamber 1 to the set value. Start the drive motor again, adjust the rotational speeds of the oil supply pump 61 and the oil return pump 62 to the set rotational speed R again, turn on the gas supply device 10, and introduce a set flow rate of sealing air into the two groups of simulated bearing cavities respectively. Observe the oil accumulation situation in the two groups of simulated bearing cavities through the observation window of the environmental chamber 1. If other test points need to be completed, this step can be repeated.

[0064] Finally, turn off the gas supply device 10, turn off the drive motor, adjust the pressure and temperature inside the environmental chamber 1 to the test atmospheric pressure and temperature, open the environmental chamber 1, and stop the test. During the test process, the boundary condition is that there is no oil accumulation in both of the two bearing simulation cavities 3.

[0065] By controlling the internal pressure and temperature of the environmental chamber 1, the operating conditions of an aero-engine under different altitudes and temperature environments are simulated. The rotational speed of the lubricating oil pump group 6 is controlled to regulate the delivery and return of the lubricating oil. Meanwhile, the air supply equipment 10 is started to simulate the air leakage conditions of the engine bearing chamber sealing device, making the test closer to the actual operating state of the aero-engine, being able to more truly reflect the actual operating conditions of the lubricating oil system's supply and return oil matching, and eliminating the influence of the differences between the standard test chamber conditions and the actual operating environment on the test results. By observing and recording the oil accumulation situation in the simulated bearing chamber, the supply and return oil matching ability of the lubricating oil system can be evaluated more accurately, providing more accurate data support for the design optimization and performance evaluation of the aero-engine lubricating oil system, and effectively improving the credibility and reliability of the test results.

[0066] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. An oil supply and return matching test device for an aero-engine lubricating oil system, characterized in that Comprising: A lubricating oil storage member (2), whose oil outlet end and oil inlet end are both communicated with a lubricating oil pump group (6), the lubricating oil pump group (6) is communicated with a simulated bearing cavity, the inlet end of the simulated bearing cavity is communicated with the oil outlet end of the lubricating oil storage member (2) through the lubricating oil pump group (6), and the outlet end of the simulated bearing cavity is communicated with the oil inlet end of the lubricating oil storage member (2) through the lubricating oil pump group (6); An air supply device (10), which is communicated with the simulated bearing cavity; An environmental chamber (1), which is enclosed, the lubricating oil storage member (2), the lubricating oil pump group (6) and the simulated bearing cavity are all installed in the environmental chamber (1), and the internal air pressure and internal temperature of the environmental chamber (1) are adapted to be adjusted by an adjusting device.

2. The oil supply and return matching test device for an aero-engine lubricating oil system according to claim 1, characterized in that, It further includes an oil-gas separation device (7), whose inlet end is communicated with the simulated bearing cavity, and whose liquid side output end is communicated with the lubricating oil storage member (2).

3. The aviation engine lubricating oil system supply and return oil matching test device according to claim 2, characterized in that, An oil mist branch is communicated between the inlet end of the oil-gas separation device (7) and the lubricating oil storage member (2).

4. The matching test device for the oil supply and return of an aero-engine lubricating oil system according to any one of claims 1 to 3, characterized in that The lubricating oil pump group (6) includes an oil supply pump (61) and an oil return pump (62), the oil supply pump (61) is installed between the inlet end of the simulated bearing cavity and the oil outlet end of the lubricating oil storage member (2), and the oil return pump (62) is installed between the outlet end of the simulated bearing cavity and the oil inlet end of the lubricating oil storage member (2).

5. The aviation engine lubricating oil system supply and return oil matching test device according to claim 4, wherein, At least two groups of the simulated bearing cavities are installed in parallel, and the oil return pump (62) is arranged corresponding to each simulated bearing cavity.

6. The matching test device for the oil supply and return of an aero-engine lubricating oil system according to any one of claims 1 to 3, characterized in that, A lubricating oil heater (8) is installed on the pipeline between the inlet end of the simulated bearing cavity and the lubricating oil pump group (6).

7. The matching test device for the oil supply and return of the aero-engine lubricating oil system according to any one of claims 1 to 3, characterized in that A pressure regulating device (4) is installed on the pipeline between the inlet end of the simulated bearing cavity and the lubricating oil pump group (6).

8. The matching test device for the oil supply and return of an aero-engine lubricating oil system according to any one of claims 1 to 3, characterized in that A pressure regulating device (4) is installed on the pipeline between the lubricating oil pump group (6) and the oil inlet end of the lubricating oil storage member (2).

9. The oil supply and return matching test device for an aero-engine lubricating oil system according to any one of claims 1 to 3, characterized in that, A driving device (5) is installed at the driving end of the lubricating oil pump group (6), and the lubricating oil pump group (6) and the driving device (5) are driven and connected through a test tooling (9).

10. A method for matching the oil supply and return of an aero-engine lubricating oil system, characterized in that, Including the following steps: Controlling the internal pressure of the environmental chamber (1) to be atmospheric pressure and the internal temperature to be ambient temperature, controlling the rotational speed value of the lubricating oil pump group (6) to be the set rotational speed, so that the lubricating oil in the lubricating oil storage member (2) is conveyed into the simulated bearing cavity; Closing the lubricating oil pump group (6) and recording the lubricating oil level in the lubricating oil storage member (2); Controlling the internal pressure of the environmental chamber (1) to be the set pressure and the internal temperature to be the set temperature, controlling the rotational speed value of the lubricating oil pump group (6) to be the set rotational speed again, and starting the air supply device (10) to introduce a set flow rate of gas into the simulated bearing cavity; Observing and recording the oil accumulation condition in the simulated bearing cavity.

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