Visual bearing cavity oil return performance test system and method

Abstract

The invention discloses a visual bearing cavity oil return performance test system and method, and belongs to the technical field of aero-engine performance tests.The visual bearing cavity oil return performance test system comprises a transparent bearing cavity visual test device used for oil-gas two-phase flow visual shooting characteristic test pieces; the oil supply subsystem is used for providing lubricating oil for the transparent bearing cavity visual test device for lubrication and cooling; the air supply subsystem is used for providing pressurized air for the transparent bearing cavity visual test device; the oil return subsystem is used for recycling lubricating oil which is lubricated and cooled in the transparent bearing cavity visual test device and realizing recycling of the lubricating oil; the ventilation subsystem is used for exhausting excess air in the bearing cavity; and the high-speed photography acquisition subsystem is used for carrying out visual shooting and analysis on the oil-gas two-phase flow state in the bearing cavity. The test device provided by the invention can observe the flow state of the oil-gas two-phase medium in the bearing cavity of the aero-engine in real time, and realizes the visualization of the oil-gas two-phase flow field of the bearing cavity.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine performance testing, and particularly relates to a visualization bearing cavity oil return performance testing experimental system and method. Background Art

[0002] The normal operation of an aero-engine depends on the effective working of the lubrication system, especially on key components such as bearings and gears. These components reduce friction and wear through lubricating oil, and take away the generated heat, thereby extending the service life. In order to collect the lubricating oil after work, an aero-engine is designed with a bearing cavity. As a core component in the lubrication system, its stability directly affects the operation of the entire system. The bearing cavity not only undertakes the function of transmitting the bearing load, but also plays a role in isolating the bearing from the external high-temperature environment and dust pollutants.

[0003] With the continuous progress of aero-engine technology, it is required to have higher rotational speed, greater thrust-to-weight ratio, lower fuel consumption, and longer service life. The working environment of the engine has become increasingly harsh, and the stability and high efficiency of the bearing cavity have become particularly critical. However, currently in the design of the bearing cavity, it still widely relies on experience, resulting in a larger volume and mass of the lubrication system, and there are still large gaps in the understanding of the oil-gas two-phase flow in the bearing cavity. The existing test methods usually have complex structures, and due to the limitations of the metal material properties, it is impossible to directly observe the oil-gas mixing phenomenon in the bearing cavity, resulting in an inability to comprehensively understand the characteristics of the oil-gas two-phase flow in the bearing cavity.

[0004] In addition, the oil return performance of the bearing cavity is affected by various factors, including rotor speed, oil supply flow rate, air supply flow rate, oil return pump speed, oil return structure, etc. The changes in different environmental load parameters and structural parameters will lead to dynamic changes in the cavity pressure, oil return pump inlet and outlet pressures, oil supply and air supply pressures, oil return oil-gas flow rate, and ventilation outlet oil-gas flow rate. Currently, traditional bearing cavity test methods often study the cavity structure as a whole, making it difficult to synchronously measure the dynamic pressure field and oil-gas flow rate, and unable to simulate the influence of different environmental loads and structural parameters on the oil return performance of the bearing cavity, resulting in limitations in the test results. The existing technologies have not been able to effectively realize the visualization of the oil-gas flow in the bearing cavity, and it is even more difficult to comprehensively evaluate the influence of environmental loads and structural parameters on the oil return performance.

[0005] Therefore, in order to deeply understand the mechanism of the oil-gas two-phase flow in the bearing cavity, especially the performance characteristics of the oil return system, there is an urgent need for an experimental method that can simulate and test the oil-gas flow and oil return performance changes in the bearing cavity under different working environments. Summary of the Invention

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A visualization test system for the oil return performance of a bearing cavity, comprising:

[0008] A transparent bearing cavity visualization test device for visualizing and photographing the characteristic test piece of the oil-gas two-phase flow;

[0009] An oil supply subsystem, the oil outlet end of which is communicated with the oil inlet end of the transparent bearing cavity visualization test device, and is used to provide lubricating oil for the transparent bearing cavity visualization test device for lubrication and cooling;

[0010] An air supply subsystem, the air outlet end of which is communicated with the air inlet end of the transparent bearing cavity visualization test device, and is used to provide pressurized air for the transparent bearing cavity visualization test device to simulate the oil-gas mixing phenomenon when the aero-engine sealing system works;

[0011] An oil return subsystem, the oil inlet end of which is communicated with the oil return end of the transparent bearing cavity visualization test device, and the oil outlet end of which is communicated with the oil inlet end of the oil supply subsystem, and is used to recover the lubricating oil that has been lubricated and cooled in the transparent bearing cavity visualization test device and realize the recycling of the lubricating oil;

[0012] A ventilation subsystem, which is communicated with the transparent bearing cavity visualization test device and is used to discharge the excess air in the bearing cavity;

[0013] A high-speed photography acquisition subsystem for visualizing, photographing and analyzing the oil-gas two-phase flow state in the bearing cavity.

[0014] Further, the transparent bearing cavity visualization test device includes:

[0015] A transparent cavity, on the outer side of which there is a high-speed servo motor control mechanism. The motor shaft of the servo motor in the high-speed servo motor control mechanism extends into the transparent cavity and is rotationally connected with the transparent cavity. A first pressure sensor is arranged on the transparent cavity;

[0016] A bearing cavity rotor, which is arranged in the transparent cavity and is installed on the motor shaft. The bearing cavity rotor includes a simulated bearing component for simulating the oil throwing function of the bearing and a simulated bearing component fixing part for fastening. The frequency converter in the high-speed servo motor control mechanism is electrically connected with the servo motor, and the frequency converter is used to adjust the rotation speed and direction of the servo motor to simulate the rotation of the bearing in the aero-engine;

[0017] An oil return structure, which is detachably connected with the transparent cavity.

[0018] Further, the oil supply subsystem includes:

[0019] Lubricating oil tank, in which a first filter screen is provided;

[0020] Oil supply pipeline, the inlet end of which is communicated with the outlet end of the lubricating oil tank, and the outlet end of which sprays oil to the bearing chamber rotor through an oil supply nozzle for providing lubricating oil for lubrication and cooling of the bearing chamber rotor. Along the oil supply direction, a first valve, a second filter screen, an oil supply pump, a turbine flowmeter, a third valve and a second pressure sensor are sequentially arranged on the oil supply pipeline.

[0021] Furthermore, an oil supply branch is further included. One end of the oil supply branch is located between the turbine flowmeter and the third valve and is communicated with the oil supply pipeline, and the other end is communicated with the inlet end of the lubricating oil tank. A second valve is arranged on the oil supply branch.

[0022] Furthermore, the oil return subsystem includes:

[0023] Labyrinth oil return tank, the top of which is communicated with an air pipeline, and a second gas flowmeter and an eleventh valve are sequentially arranged on the air pipeline along the gas discharge direction;

[0024] Mixed oil and gas recovery pipeline, the inlet end of which is communicated with the oil return end of the transparent cavity, and the outlet end of which is communicated with the inlet end of the labyrinth oil return tank. Along the oil return direction, a sixth valve, an eighth valve, a fourth pressure sensor, an oil return pump, a fifth pressure sensor and a ninth valve are sequentially arranged on the mixed oil and gas recovery pipeline. A seventh valve is arranged between the sixth valve and the eighth valve;

[0025] Lubricating oil recovery pipeline, the inlet end of which is communicated with the first oil outlet end of the labyrinth oil return tank, and the outlet end of which is communicated with the inlet end of the lubricating oil tank. A twelfth valve is arranged on the lubricating oil recovery pipeline;

[0026] Oil tank, which is communicated with the second oil outlet end of the labyrinth oil return tank through an oil weighing pipeline, and a tenth valve is arranged on the oil weighing pipeline;

[0027] Weighing device, which is arranged at the bottom of the oil tank.

[0028] Furthermore, the air supply subsystem includes:

[0029] Air compressor;

[0030] An air supply pipeline, the inlet end of the air supply pipeline is connected to the outlet end of the air compressor, the outlet end of the air supply pipeline is connected to the inlet end of the transparent bearing cavity visualization test device, and a first pressure stabilizing tank and a second pressure stabilizing tank are connected in parallel on the air supply pipeline. A fourth valve, a fifth valve, a third pressure sensor and a first gas mass flowmeter are sequentially arranged on the air supply pipeline between the first pressure stabilizing tank, the second pressure stabilizing tank and the transparent bearing cavity visualization test device along the air supply direction.

[0031] Further, the ventilation subsystem includes:

[0032] An oil and gas separator, a separated lubricating oil collecting pipe is arranged at the bottom of the oil and gas separator, and a fourteenth valve is arranged on the separated lubricating oil collecting pipe;

[0033] A first oil and gas discharge pipe, the inlet end of the first oil and gas discharge pipe is connected to the outlet end of the transparent bearing cavity visualization test device, and the outlet end of the first oil and gas discharge pipe is connected to the inlet end of the oil and gas separator;

[0034] A second oil and gas discharge pipe, the first end of the second oil and gas discharge pipe is connected to the outlet end of the oil and gas separator, the second end of the second oil and gas discharge pipe is connected to the atmosphere, and a sixth pressure sensor, a third gas mass flowmeter and a fifteenth valve are sequentially arranged on the second oil and gas discharge pipe along the outlet direction;

[0035] A waste liquid bucket, the waste liquid bucket is located directly below the second end of the second oil and gas discharge pipe for collecting waste liquid.

[0036] Further, the high-speed photography acquisition subsystem includes:

[0037] A high-speed camera, the high-speed camera is arranged outside the transparent bearing cavity visualization test device, and is used to capture the state of the oil-gas two-phase flow in the transparent bearing cavity and upload the captured images to a computer for image editing and flow analysis;

[0038] An LED auxiliary light source, the LED auxiliary light source is arranged on one side of the high-speed camera for providing illumination to ensure the image quality during the visualization process.

[0039] A method for testing the oil return performance of a visualization bearing cavity, using the visualization bearing cavity oil return performance test system described in any one of the above, the method includes the following steps:

[0040] S10. Install the bearing cavity visualization feature test piece on the transparent bearing cavity visualization test device, and at the same time connect the oil supply subsystem, the air supply subsystem, the oil return subsystem, the ventilation subsystem to the transparent bearing cavity visualization test device, and adjust the high-speed photography subsystem;

[0041] S20. Start the high-speed servo motor control mechanism to regulate the rotor in the bearing cavity to reach the operating speed of the aero-engine bearing. Provide lubricating oil for the transparent bearing cavity visualization test device through the oil supply subsystem for lubrication and cooling. Provide pressurized air for the transparent bearing cavity visualization test device through the air supply subsystem to simulate sealed air intake. Recover the remaining lubricating oil after the operation of the transparent bearing cavity visualization test device through the oil return subsystem for recycling. Discharge the excess air in the transparent bearing cavity visualization test device through the ventilation subsystem. Take pictures of the oil-gas two-phase flow field distribution in the bearing cavity through the high-speed photography subsystem.

[0042] Furthermore, the oil return efficiency

[0043] where Q oil-sca is the lubricating oil flow rate at the oil return outlet, and Q oil-in is the lubricating oil flow rate provided by the oil supply system to the transparent bearing cavity visualization test device. Evaluate the oil return performance of the bearing cavity under different working conditions according to the magnitude of the oil return efficiency. After the test is completed, open the seventh valve and weigh the oil volume in the cavity to assist in evaluating the oil return performance of the bearing cavity.

[0044] Beneficial effects:

[0045] By adjusting different pressures in the bearing cavity, the rotational speed of the bearing rotor, the oil supply flow rate, the air supply flow rate, the rotational speed of the oil return pump, and replacing different oil return structures, the present invention simulates the working states of the bearing cavity under different working conditions. By arranging multiple pressure and flow measurement points in the test pipeline, the pressure distribution and oil-gas flow rate distribution in the system are monitored and measured in real time, so as to obtain the pressure data, oil return flow rate and ventilation air volume of the bearing cavity under different working conditions, and reveal the response laws of the pressure distribution and oil-gas flow rate in the system under different working states, providing an important basis for evaluating the oil return performance of the bearing cavity under different working conditions.

[0046] The test device provided by the present invention can observe the flow state of the oil-gas two-phase medium in the aero-engine bearing cavity in real time and realize the visualization of the oil-gas two-phase flow field in the bearing cavity.

[0047] The present invention not only has high precision and operability, but also has significant advantages such as simple structure, modular design, strong replaceability, convenient operation and low cost.

[0048] The present invention can quickly replace the oil return structure according to different test requirements, so as to adapt to the bearing cavity structures of different models of aero-engines and simulate their lubrication and oil return performances under different working conditions.

[0049] The design of the test device provided by the present invention ensures high-efficiency functionality and has low operation and maintenance costs. Description of the Drawings

[0050] Figure 1 This is a schematic structural diagram of the test device for visualizing the oil return performance of the bearing cavity of the present invention.

[0051] Figure 2 This is an installation schematic diagram of the bearing cavity rotor of the present invention.

[0052] Figure 3 This is a curve graph showing the change of the oil return efficiency of the bearing cavity with the rotational speed of the bearing cavity rotor in the present invention.

[0053] Among them, 1. Transparent bearing cavity visualization test device; 2. Oil supply subsystem; 3. Air supply subsystem; 4. Oil return subsystem; 5. Ventilation subsystem; 6. High-speed photography acquisition subsystem; 11. Transparent cavity; 12. Bearing cavity rotor; 13. Oil return structure; 14. First pressure sensor; 15. High-speed servo motor control mechanism; 151. Servo motor; 152. Frequency converter controller; 153. Motor shaft; 21. Oil sump tank; 22. First filter screen; 23. First valve; 24. Second filter screen; 25. Oil supply pump; 26. Turbine flowmeter; 27. Second valve; 28. Third valve; 29. Second pressure sensor; 210. Oil supply nozzle; 31. Air compressor; 32. First pressure stabilizing tank; 33. Second pressure stabilizing tank; 34. Fourth valve; 35. Fifth valve; 36. Third pressure sensor; 37. First gas mass flowmeter; 41. Sixth valve; 42. Seventh valve; 43. Eighth valve; 44. Fourth pressure sensor; 45. Oil return pump; 46. Fifth pressure sensor; 47. Ninth valve; 48. Labyrinth oil return tank; 49. Tenth valve; 410. Oil tank; 411. Weighing device; 412. Second gas mass flowmeter; 413. Eleventh valve; 414; Twelfth valve; 51. Thirteenth valve; 52. Oil-gas separator; 53. Fourteenth valve; 54. Sixth pressure sensor; 55. Third gas mass flowmeter; 56. Fifteenth valve; 57. Waste liquid bucket; 61. High-speed camera; 62. Computer; 63. LED auxiliary light source; 121. Simulated bearing component; 122. Simulated bearing component fixing part; 123. Fastening bolt. Detailed implementation manners

[0054] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.

[0055] This part will describe in detail the specific embodiments of the present invention. The preferred embodiments of the present invention are shown in the drawings. The function of the drawings is to supplement the description of the text part of the specification, enabling people to intuitively and vividly understand each technical feature and the overall technical solution of the present invention, but it should not be construed as a limitation on the protection scope of the present invention.

[0056] In the description of the present invention, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc., it is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention.

[0057] In the description of the present invention, the meaning of "several" is one or more, the meaning of "multiple" is two or more, "greater than", "less than", "exceeding", etc. are understood as not including the original number, and "above", "below", "within", etc. are understood as including the original number. If the first and second are described only for the purpose of distinguishing technical features, they should not be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or the sequence relationship of the indicated technical features.

[0058] In the description of the present invention, unless otherwise clearly defined, words such as "set", "installed", "connected", etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meaning of the above words in the present invention in combination with the specific content of the technical solution.

[0059] Embodiment 1

[0060] Reference Figures 1 - 3 , a visualization test system for the oil return performance of a bearing cavity, comprising:

[0061] A transparent bearing cavity visualization test device 1, used for visual shooting of the characteristics of the test piece for the oil-gas two-phase flow;

[0062] An oil supply subsystem 2, the oil outlet end of the oil supply subsystem 2 is communicated with the oil inlet end of the transparent bearing cavity visualization test device 1, and is used to provide lubricating oil for the transparent bearing cavity visualization test device 1 for lubrication and cooling;

[0063] An air supply subsystem 3, the air outlet end of the air supply subsystem 3 is communicated with the air inlet end of the transparent bearing cavity visualization test device 1, and is used to provide pressurized air for the transparent bearing cavity visualization test device 1 to simulate the oil-gas mixing phenomenon when the aviation engine sealing system works;

[0064] An oil return subsystem 4, the oil inlet end of the oil return subsystem 4 is communicated with the oil return end of the transparent bearing cavity visualization test device 1, and the oil outlet end of the oil return subsystem 4 is communicated with the oil inlet end of the oil supply subsystem 2, and is used to recover the lubricating oil that has been lubricated and cooled in the transparent bearing cavity visualization test device 1 and realize the recycling of the lubricating oil;

[0065] A ventilation subsystem 5, which is communicated with the transparent bearing cavity visualization test device 1 and is used to discharge the excess air in the bearing cavity;

[0066] The high-speed photography acquisition subsystem 6 is used for visually photographing and analyzing the oil-gas two-phase flow state in the bearing cavity.

[0067] The test device provided by the present invention can observe the flow state of the oil-gas two-phase medium in the aero-engine bearing cavity in real time, and realize the visualization of the oil-gas two-phase flow field in the bearing cavity.

[0068] The test device provided by the present invention not only has high precision and operability, but also has significant advantages such as simple structure, modular design, strong replaceability, convenient operation and low cost. It can quickly replace the oil return structure according to different test requirements, so as to adapt to the bearing cavity structures of different models of aero-engines and simulate their lubrication and oil return performances under different working conditions.

[0069] The design of the test device provided by the present invention ensures high-efficiency functionality and has low operation and maintenance costs.

[0070] In this embodiment, the transparent bearing cavity visualization test device 1 includes:

[0071] A transparent cavity 11, on the outer side of the transparent cavity 11, there is a high-speed servo motor control mechanism 15. The motor shaft 153 of the servo motor 151 in the high-speed servo motor control mechanism 15 extends into the transparent cavity 11 and is rotationally connected to the transparent cavity 11. The transparent cavity 11 is provided with a first pressure sensor 14;

[0072] Preferably, the transparent cavity 11 is made of plexiglass material, which is used to observe the flow state of the oil-gas two-phase medium inside the bearing cavity and realize the visualization of the oil-gas two-phase flow field. At the same time, the transparent cavity 11 is equipped with a first pressure sensor 14 for monitoring the pressure change inside the cavity.

[0073] A bearing cavity rotor 12 is arranged inside the transparent cavity 11 and is installed on the motor shaft 153. The bearing cavity rotor 12 includes a simulated bearing component 121 for simulating the oil slinging function of the bearing and a simulated bearing component fixing part 122 for fastening. The frequency converter 152 in the high-speed servo motor control mechanism 15 is electrically connected to the servo motor 151. The frequency converter 152 is used to adjust the rotation speed and direction of the servo motor 151 to simulate the rotation of the bearing in the aero-engine;

[0074] During specific implementation, the simulated bearing component 121 and the simulated bearing component fixing part 122 are connected by fastening bolts 123.

[0075] During specific implementation, an oil slinger hole for simulating the actual oil slinging function of the bearing is provided on the simulated bearing component 121 to simulate the discrete effect of the high-speed bearing on the lubricating oil. The bearing chamber rotor 12 is regulated by the high-speed servo motor control mechanism 15, and its rotation speed and direction are adjusted through the frequency converter 152 to simulate the working state of the bearing in an aeroengine under high-speed rotation. The bearing chamber rotor 12 is installed in a transparent cavity to directly observe the oil slinging process of the bearing chamber rotor 12 and the flow state of the oil-gas two-phase medium in the cavity, meeting the visualization shooting requirements of the high-speed photography system.

[0076] An oil return structure 13, and the oil return structure 13 is detachably connected to the transparent cavity 11.

[0077] During specific implementation, the oil return structure 13 is installed by grooving on the transparent cavity 11. The oil return structure 13 can be freely embedded into the transparent cavity 11, thus realizing the detachable function. The lubricating oil after lubricating the bearing chamber rotor 12 flows into the oil return pool or oil return pipeline in the oil return structure 11 to realize the collection of the lubricating oil. During processing, by ensuring that the external dimensions of the oil return structure 13 remain unchanged and changing the settings of the oil return pool or pipeline with different shapes, the detachable replacement of different oil return structures 13 can be realized. The detachable oil return structure 13 can realize the replacement and installation functions of different oil return structures, and is used to explore the influence law of different structural parameters on the oil return performance of the bearing chamber. At the same time, a rubber gasket is added between the detachable oil return structure 13 and the transparent cavity 11 to realize the sealing function.

[0078] The present invention simulates the working state of the aeroengine bearing chamber under different environmental loads and structural parameters by precisely regulating the rotation speed of the bearing chamber rotor, the oil supply flow rate, the gas supply flow rate, and the rotation speed of the oil return pump, and replacing different oil return structures as needed, so as to reproduce various working conditions under actual working conditions.

[0079] In this embodiment, the oil supply subsystem 2 includes:

[0080] An oil storage tank 21, and a first filter screen 22 is arranged in the oil storage tank 21;

[0081] An oil supply pipeline, the inlet end of the oil supply pipeline is communicated with the outlet end of the oil storage tank 21, and the outlet end of the oil supply pipeline sprays oil on the bearing chamber rotor 12 through an oil supply nozzle 210 for providing lubricating oil for lubricating and cooling the bearing chamber rotor 12. The oil supply pipeline is sequentially provided with a first valve 23, a second filter screen 24, an oil supply pump 25, a turbine flowmeter 26, a third valve 28, and a second pressure sensor 29 along the oil supply direction.

[0082] In this embodiment, the turbine flowmeter 26 and the second pressure sensor 29 arranged between the oil supply pump 25 and the oil supply nozzle 210 are used to measure the lubricating oil flow rate in the oil supply pipeline and the inlet pressure on the oil supply side of the bearing chamber.

[0083] In this embodiment, a first filter screen 22 is provided inside the lubricating oil tank 21 to filter the lubricating oil entering the lubricating oil tank 21 from the oil supply branch and the lubricating oil recovery pipeline, ensuring the cleanliness of the lubricating oil. A second filter screen 24 is provided between the lubricating oil tank 21 and the oil supply pump 25 to filter the lubricating oil flowing into the oil supply pipeline, preventing metal particles and other impurities from entering the oil return pipeline and avoiding damaging the turbine sensor of the turbine flowmeter 26 and blocking the oil supply nozzle 210.

[0084] During specific implementation, the oil supply pump 25 pumps the lubricating oil out of the lubricating oil tank 21 and enters the transparent bearing chamber visualization test device 1 through the oil supply pipeline. The motor frequency converter of the oil supply pump 25 adjusts the pump speed to control the oil supply flow rate.

[0085] In this embodiment, an oil supply branch is further included. One end of the oil supply branch is located between the turbine flowmeter 26 and the third valve 28 and is communicated with the oil supply pipeline, and the other end is communicated with the oil inlet end of the lubricating oil tank 21. A second valve 27 is provided on the oil supply branch. The oil supply branch is used to adjust the oil supply flow rate. Opening the second valve 27 can recycle the lubricating oil.

[0086] During specific implementation, during the test, first keep the first valve 23 and the second valve 27 open, close the third valve 28, adjust the oil supply pump 25 to a certain speed to meet the oil supply flow rate requirement under a certain test condition, and enable the lubricating oil to achieve internal circulation on the oil supply branch. Opening the second valve 27 can recycle the lubricating oil to the lubricating oil tank. After adjustment, close the second valve 27 and open the third valve 28. The lubricating oil in the oil supply pipeline finally enters the transparent bearing chamber visualization test device 1 through the oil supply nozzle 210.

[0087] In this embodiment, the oil return subsystem 4 includes:

[0088] A labyrinth oil return tank 48. An air pipeline is communicated with the top of the labyrinth oil return tank 48. A second gas flowmeter 412 and an eleventh valve 413 are sequentially arranged on the air pipeline along the gas discharge direction;

[0089] During specific implementation, the labyrinth oil return tank 48 realizes oil-gas separation through a multi-layer labyrinth structure.

[0090] A mixed oil-gas recovery pipeline. The oil inlet end of the mixed oil-gas recovery pipeline is communicated with the oil return end of the transparent cavity 11, and the oil outlet end of the mixed oil-gas recovery pipeline is communicated with the oil inlet end of the labyrinth oil return tank 48. A sixth valve 41, an eighth valve 43, a fourth pressure sensor 44, an oil return pump 45, a fifth pressure sensor 46 and a ninth valve 47 are sequentially arranged on the mixed oil-gas recovery pipeline along the oil return direction. A seventh valve 42 is arranged between the sixth valve 41 and the eighth valve 43;

[0091] The lubricating oil recovery pipeline, the oil inlet end of the lubricating oil recovery pipeline is communicated with the first oil outlet end of the labyrinth return oil tank 48, the oil outlet end of the lubricating oil recovery pipeline is communicated with the oil inlet end of the lubricating oil tank 21, and the twelfth valve 414 is arranged on the lubricating oil recovery pipeline;

[0092] The oil tank 410, the oil tank 410 is communicated with the second oil outlet end of the labyrinth return oil tank 48 through the oil weighing pipeline, and the tenth valve 49 is arranged on the oil weighing pipeline;

[0093] The weighing device 411, the weighing device 411 is arranged at the bottom of the oil tank 410.

[0094] In this embodiment, on both sides of the inlet end and the outlet end of the oil return pump 45, a fourth pressure sensor 44 and a fifth pressure sensor 46 are respectively arranged for monitoring the changes in the inlet pressure and the outlet pressure of the oil return pump 45. A second gas flowmeter 412 is arranged on the air pipeline at the top of the labyrinth return oil tank 48 for measuring the air flow rate at the oil return outlet. A oil tank 410 and a weighing device 411 are arranged on the oil weighing pipeline at the bottom of the labyrinth return oil tank 48 for measuring the lubricating oil flow rate at the oil return outlet.

[0095] In this embodiment, the oil return pump 45 pumps the mixed oil and gas from the transparent bearing chamber visualization test device 1 into the labyrinth return oil tank 48. The labyrinth return oil tank 48 realizes oil and gas separation through a multi-layer labyrinth structure. The oil weighing pipeline is used to send the recovered lubricating oil to the oil tank 410, and the flow rate of the lubricating oil is accurately measured by the weighing device 411; the lubricating oil recovery pipeline returns the separated lubricating oil to the lubricating oil tank 21 to ensure the recycling of the lubricating oil. The top of the labyrinth return oil tank 48 is connected to the air pipeline and leads directly to the atmosphere, and the air flow rate separated in the oil return system is measured by the second gas flowmeter 412.

[0096] During the specific implementation, during the test, in order to accurately obtain the oil return flow rate, it is necessary to first keep the ninth valve 47 and the twelfth valve 414 open, keep the tenth valve 49 closed. After the system runs stably, observe that the height of the lubricating oil liquid level in the labyrinth return oil tank 48 is stable. At the same time, close the twelfth valve 414 and open the tenth valve 49, and use the weighing device 411 to accurately measure the oil return flow rate. The top of the labyrinth return oil tank 48 is connected to the air pipeline and leads directly to the atmosphere. Keep the eleventh valve 413 open, and measure the air flow rate separated in the oil return system through the second gas flowmeter 412.

[0097] In this embodiment, the air supply subsystem 3 includes:

[0098] An air compressor 31;

[0099] An air supply pipeline, the intake end of the air supply pipeline is connected to the outlet end of the air compressor 31, the outlet end of the air supply pipeline is connected to the intake end of the transparent bearing cavity visualization test device 1, and a first pressure stabilizing tank 32 and a second pressure stabilizing tank 33 are connected in parallel on the air supply pipeline to provide a large flow of pressurized air to simulate the intake air volume of the bearing cavity seal. On the air supply pipeline between the first pressure stabilizing tank 32, the second pressure stabilizing tank 33 and the transparent bearing cavity visualization test device 1, a fourth valve 34, a fifth valve 35, a third pressure sensor 36 and a first gas mass flowmeter 37 are arranged in sequence along the air supply direction.

[0100] In this embodiment, a third pressure sensor 36 and a first gas mass flowmeter 37 are arranged between the first pressure stabilizing tank 32, the second pressure stabilizing tank 33 and the transparent cavity 11 to measure the inlet pressure on the air supply side of the bearing cavity and the air flow rate of the air supply pipeline.

[0101] In this embodiment, during the air supply process, the air compressor 31 is turned on to inflate the first pressure stabilizing tank 32 and the second pressure stabilizing tank 33. After the operation is stable, the fourth valve 34 is kept fully open, the fifth valve 35 is slowly adjusted, and the changes in the readings of the third pressure sensor 36 and the first gas mass flowmeter 37 are observed to control the air flow rate entering the transparent bearing cavity visualization test device 1.

[0102] During the test of the present invention, the inlet pressures of the oil supply side and the air supply side of the bearing cavity, the cavity pressure, and the pressure data at the inlet and outlet of the oil return pump can be accurately measured. These data are helpful for analyzing and determining the pressure change law of the bearing cavity system. In addition, the test device of the present invention can also synchronously measure the oil and gas flow rates at the oil return outlet and the ventilation outlet, and monitor their dynamic changes in real time, so as to deeply understand the change law of the oil return performance of the bearing cavity.

[0103] In this embodiment, the ventilation subsystem 5 includes:

[0104] An oil and gas separator 52, a separated lubricating oil collecting pipe is arranged at the bottom of the oil and gas separator 52, and a fourteenth valve 53 is arranged on the separated lubricating oil collecting pipe;

[0105] A first oil and gas discharge pipe, the intake end of the first oil and gas discharge pipe is connected to the outlet end of the transparent bearing cavity visualization test device 1, and the outlet end of the first oil and gas discharge pipe is connected to the intake end of the oil and gas separator 52;

[0106] A second oil and gas discharge pipe, the first end of the second oil and gas discharge pipe is connected to the outlet end of the oil and gas separator 52, the second end of the second oil and gas discharge pipe is connected to the atmosphere, and a sixth pressure sensor 54, a third gas mass flowmeter 55 and a fifteenth valve 56 are arranged in sequence along the outlet direction of the second oil and gas discharge pipe;

[0107] The waste liquid barrel 57 is located directly below the second end of the second oil and gas discharge pipe and is used to collect waste liquid.

[0108] In this embodiment, on the second oil and gas discharge pipeline between the oil and gas separation box 52 in the ventilation subsystem 5 and the atmosphere, a sixth pressure sensor 54 and a third gas mass flowmeter 55 are provided to measure the ventilation outlet pressure and the air flow rate flowing through the ventilation outlet.

[0109] In this embodiment, the ventilation subsystem 5 is used to discharge the excess air in the bearing cavity and recover the escaped lubricating oil. The oil and gas separator 52 can effectively separate the oil and gas mixture in the ventilation pipeline. The separated lubricating oil deposits at the bottom of the oil and gas separator 52. Opening the fourteenth valve 53 can discharge the separated lubricating oil, and the separated air is discharged through the top of the oil and gas separator 52.

[0110] During specific implementation, after the oil and gas mixture escaping from the ventilation port enters the oil and gas separator 52, the oil and gas mixed medium is separated. The separated lubricating oil deposits at the bottom of the oil and gas separator 52. Opening the fourteenth valve 53 can discharge the separated lubricating oil, and the separated air is discharged to the atmosphere through the top of the oil and gas separator 52. At the same time, the waste liquid barrel 57 can collect a small amount of lubricating oil that may escape.

[0111] In this embodiment, the high-speed photography acquisition subsystem 6 includes:

[0112] A high-speed camera 61 is arranged outside the transparent bearing cavity visualization test device 1 and is used to capture the state of the oil and gas two-phase flow in the transparent bearing cavity and upload the captured images to the computer 62 for image editing and flow analysis;

[0113] An LED auxiliary light source 63 is arranged on one side of the high-speed camera 61 and is used to provide illumination to ensure the image quality during the visualization process.

[0114] Embodiment 2

[0115] This embodiment provides a method for testing the oil return performance of a visualization bearing cavity, using the visualization bearing cavity oil return performance test system in Embodiment 1. The method includes the following steps:

[0116] S10. Install the bearing cavity visualization characteristic test piece on the transparent bearing cavity visualization test device 1, and at the same time connect the oil supply subsystem 2, the air supply subsystem 3, the oil return subsystem 4, and the ventilation subsystem 5 to the transparent bearing cavity visualization test device 1, and adjust the high-speed photography acquisition subsystem 6;

[0117] S20. Start the high-speed servo motor control mechanism 15 to regulate the bearing chamber rotor 12 to reach the operating speed of the aero-engine bearing. Provide lubricating oil for the transparent bearing chamber visualization test device 1 through the oil supply subsystem 2 for lubrication and cooling. Provide pressurized air for the transparent bearing chamber visualization test device 1 through the air supply subsystem 3 to simulate sealed air intake. Recover the remaining lubricating oil after the operation of the transparent bearing chamber visualization test device 1 through the oil return subsystem 4 for recycling. Discharge the excess air in the transparent bearing chamber visualization test device 1 through the ventilation subsystem 5. Capture the distribution of the oil-gas two-phase flow field in the bearing chamber through the high-speed photography acquisition subsystem 6.

[0118] Maintain for a predetermined time. In this embodiment, it is necessary to measure the oil return flow using the weighing device 411, and the holding time can be set to 2 Min.

[0119] In this embodiment, the oil return efficiency

[0120] where Q oil-sca is the lubricating oil flow rate at the oil return outlet, and Q oil-in is the lubricating oil flow rate provided by the oil supply subsystem 2 to the transparent bearing chamber visualization test device 1. Evaluate the oil return performance of the bearing chamber under different operating conditions according to the magnitude of the oil return efficiency. After the test is completed, open the seventh valve 42 to weigh the oil volume in the chamber to assist in evaluating the oil return performance of the bearing chamber.

[0121] Specifically in implementation, this embodiment selects a bearing chamber structure for test and measurement. Figure 3 The curve graph showing the change of the oil return efficiency of the bearing chamber with the rotational speed of the bearing chamber rotor under the design conditions where the rotational speed of the different bearing chamber rotors 12 changes is given. In addition, during the test and measurement process, first keep the seventh valve 42 closed, keep the sixth valve 41 and the eighth valve 43 open. After the test is over, simultaneously stop the operation of the motor of the lubricating oil pump 25 of the bearing chamber rotor 12, and at the same time close the fifth valve 35, the third valve 28, and the eighth valve 43. After the liquid level in the transparent cavity 11 is stable, open the seventh valve 42 to weigh the oil volume in the chamber to assist in evaluating the oil return performance of the bearing chamber.

[0122] The above is only a preferred embodiment of the present invention, and does not impose any limitation on the technical scope of the present invention. Therefore, any minor modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present invention still fall within the scope of the technical solution of the present invention.

Claims

1. A visual bearing chamber oil return performance test system, characterized in that: include: A transparent bearing cavity visualization test device (1) is used for visually photographing characteristic test pieces of oil-gas two-phase flow; An oil supply subsystem (2), the oil outlet end of the oil supply subsystem (2) being in communication with the oil inlet end of the transparent bearing cavity visualization test device (1), and being used to provide lubricating oil to the transparent bearing cavity visualization test device (1) for lubrication and cooling; An air supply subsystem (3), the air outlet of the air supply subsystem (3) being connected to the air inlet of the transparent bearing cavity visualization test device (1), and being used to provide pressurized air to the transparent bearing cavity visualization test device (1) to simulate the oil-gas mixing phenomenon when the sealing system of the aircraft engine is working; An oil return subsystem (4), wherein the oil inlet end of the oil return subsystem (4) is connected to the oil return end of the transparent bearing cavity visualization test device (1), and the oil outlet end of the oil return subsystem (4) is connected to the oil inlet end of the oil supply subsystem (2), and is used to recover the lubricating oil in the transparent bearing cavity visualization test device (1) after lubrication and cooling, and realize the recycling of the lubricating oil; A ventilation subsystem (5), connected to the transparent bearing cavity visualization test device (1), and used for exhausting excess air in the bearing cavity; The high-speed photography acquisition subsystem (6) is used to visualize and analyze the oil-gas two-phase flow state in the bearing cavity.

2. The visual bearing chamber oil return performance test system according to claim 1 is characterized in that: The transparent bearing cavity visualization test device (1) comprises: A transparent cavity (11), a high-speed servo motor control mechanism (15) is arranged outside the transparent cavity (11), a motor shaft (153) of a servo motor (151) in the high-speed servo motor control mechanism (15) extends into the transparent cavity (11) and is rotatably connected to the transparent cavity (11), and a first pressure sensor (14) is arranged on the transparent cavity (11); A bearing cavity rotor (12), the bearing cavity rotor (12) being arranged in the transparent cavity (11) and mounted on the motor shaft (153), the bearing cavity rotor (12) comprising a simulated bearing component (121) simulating a bearing oil throwing function and a simulated bearing component fixing member (122) for fastening, a frequency conversion controller (152) in the high-speed servo motor control mechanism (15) being electrically connected to the servo motor (151), the frequency conversion controller (152) being used to adjust the rotation speed and direction of the servo motor (151) to simulate the bearing rotation in an aircraft engine; An oil return structure (13), wherein the oil return structure (13) is detachably connected to the transparent cavity (11).

3. The visual bearing chamber oil return performance test system according to claim 2 is characterized in that: The oil supply subsystem (2) comprises: A lubricating oil tank (21), wherein a first filter screen (22) is arranged in the lubricating oil tank (21); An oil supply pipeline, wherein the oil inlet end of the oil supply pipeline is connected to the oil outlet end of the lubricating oil tank (21), and the oil outlet end of the oil supply pipeline sprays oil to the bearing cavity rotor (12) through an oil supply nozzle (210) to provide lubricating oil for lubrication and cooling of the bearing cavity rotor (12). The oil supply pipeline is sequentially provided with a first valve (23), a second filter (24), an oil supply pump (25), a turbine flowmeter (26), a third valve (28) and a second pressure sensor (29) along the oil supply direction.

4. The visual bearing chamber oil return performance test system according to claim 3 is characterized in that: It also includes an oil supply branch, one end of which is located between the turbine flowmeter (26) and the third valve (28) and is connected to the oil supply pipeline, and the other end is connected to the oil inlet end of the lubricating oil tank (21), and a second valve (27) is provided on the oil supply branch.

5. The visual bearing chamber oil return performance test system according to claim 3 is characterized in that: The oil return subsystem (4) comprises: A labyrinth oil return tank (48), wherein the top of the labyrinth oil return tank (48) is connected to an air pipeline, and a second gas flow meter (412) and an eleventh valve (413) are sequentially arranged on the air pipeline along the gas discharge direction; a mixed oil and gas recovery pipeline, wherein the oil inlet end of the mixed oil and gas recovery pipeline is connected to the oil return end of the transparent cavity (11), the oil outlet end of the mixed oil and gas recovery pipeline is connected to the oil inlet end of the labyrinth oil return tank (48), a sixth valve (41), an eighth valve (43), a fourth pressure sensor (44), an oil return pump (45), a fifth pressure sensor (46) and a ninth valve (47) are sequentially arranged along the oil return direction of the mixed oil and gas recovery pipeline, and a seventh valve (42) is arranged between the sixth valve (41) and the eighth valve (43); a lubricating oil recovery pipeline, wherein an oil inlet end of the lubricating oil recovery pipeline is connected to a first oil outlet end of the labyrinth oil return tank (48), an oil outlet end of the lubricating oil recovery pipeline is connected to an oil inlet end of the lubricating oil tank (21), and a twelfth valve (414) is provided on the lubricating oil recovery pipeline; An oil tank (410), the oil tank (410) being connected to the second oil outlet end of the labyrinth oil return tank (48) via an oil weighing pipeline, and a tenth valve (49) is provided on the oil weighing pipeline; A weighing device (411), wherein the weighing device (411) is arranged at the bottom of the oil tank (410).

6. The visual bearing chamber oil return performance test system according to claim 1 is characterized in that: The air supply subsystem (3) comprises: Air compressor (31); An air supply pipeline, wherein the air inlet end of the air supply pipeline is connected to the air outlet end of the air compressor (31), the air outlet end of the air supply pipeline is connected to the air inlet end of the transparent bearing cavity visualization test device (1), and a first pressure stabilizing tank (32) and a second pressure stabilizing tank (33) are connected in parallel on the air supply pipeline, and a fourth valve (34), a fifth valve (35), a third pressure sensor (36) and a first gas mass flow meter (37) are sequentially arranged along the air supply direction on the air supply pipeline between the first pressure stabilizing tank (32), the second pressure stabilizing tank (33) and the transparent bearing cavity visualization test device (1).

7. The visual bearing chamber oil return performance test system according to claim 1 is characterized in that: The ventilation subsystem (5) comprises: An oil-gas separator (52), wherein a separation lubricating oil collecting pipe is provided at the bottom of the oil-gas separator (52), and a fourteenth valve (53) is provided on the separation lubricating oil collecting pipe; a first oil and gas discharge pipe, wherein the air inlet end of the first oil and gas discharge pipe is connected to the air outlet end of the transparent bearing cavity visualization test device (1), and the air outlet end of the first oil and gas discharge pipe is connected to the air inlet end of the oil and gas separator (52); a second oil and gas discharge pipe, wherein a first end of the second oil and gas discharge pipe is connected to a gas outlet end of the oil and gas separator (52), a second end of the second oil and gas discharge pipe is connected to the atmosphere, and a sixth pressure sensor (54), a third gas mass flow meter (55) and a fifteenth valve (56) are sequentially arranged on the second oil and gas discharge pipe along a gas outlet direction; A waste liquid bucket (57), the waste liquid bucket (57) is located directly below the second end of the second oil and gas discharge pipe and is used to collect waste liquid.

8. The visual bearing chamber oil return performance test system according to claim 1 is characterized in that: The high-speed photography acquisition subsystem (6) includes: A high-speed camera (61), the high-speed camera (61) being arranged outside the transparent bearing cavity visualization test device (1), and being used to capture the state of the oil-gas two-phase flow in the transparent bearing cavity, and uploading the captured images to a computer (62) for image editing and flow analysis; An LED auxiliary light source (63) is arranged on one side of the high-speed camera (61) and is used to provide lighting to ensure the image quality of the visualization process.

9. A visual bearing cavity oil return performance test method, characterized in that: Using the visual bearing cavity oil return performance test system according to any one of claims 1 to 8, the method comprises the following steps: S10, installing the bearing cavity visualization feature test piece on the transparent bearing cavity visualization test device (1), connecting the oil supply subsystem (2), the air supply subsystem (3), the oil return subsystem (4), and the ventilation subsystem (5) to the transparent bearing cavity visualization test device (1), and adjusting the high-speed photography subsystem (6); S20, start the high-speed servo motor control mechanism (15) to adjust the bearing cavity rotor (12) to reach the operating speed of the aircraft engine bearing, provide lubricating oil to the transparent bearing cavity visualization test device (1) through the oil supply subsystem (2) for lubrication and cooling, provide pressurized air to the transparent bearing cavity visualization test device (1) through the air supply subsystem (3) to simulate sealed air intake, recover the remaining lubricating oil of the transparent bearing cavity visualization test device (1) after operation through the oil return subsystem (4) for recycling, discharge the excess air in the transparent bearing cavity visualization test device (1) through the ventilation subsystem (5), and photograph the oil-gas two-phase flow field distribution in the bearing cavity through the high-speed photography subsystem (6).

10. The visual bearing chamber oil return performance test method according to claim 9 is characterized in that: Oil return efficiency Where Q oil-sca is the oil flow rate at the return oil outlet, Q oil-in The lubricating oil flow rate provided by the oil supply system (2) to the transparent bearing cavity visualization test device (1) is used to evaluate the oil return performance of the bearing cavity under different working conditions according to the oil return efficiency. After the test is completed, the seventh valve (42) is opened to measure the amount of oil stored in the cavity to assist in evaluating the oil return performance of the bearing cavity.

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