Aero-engine bearing cavity tester and test system and test method thereof

Abstract

The invention belongs to the technical field of aero-engine bearing cavity testing, and particularly relates to an aero-engine bearing cavity tester and a testing system and method thereof, and the aero-engine bearing cavity tester comprises a housing, an oil return pool construction block, a front cover plate, a rear cover plate, a bearing simulation rotating disc, and a driving rotating shaft. A bearing cavity simulation space and an oil return pool structure space communicated with the bearing cavity simulation space are formed in the shell; an oil supply port, a ventilation port and an air inlet which are communicated with the bearing cavity simulation space are formed in the side wall of the shell; an oil return port communicated with the oil return pool structure space is formed in the side wall of the pressure measuring hole shell; the oil return pool construction block is arranged in the oil return pool construction space, an oil return simulation pool is formed between the oil return pool construction block and the bearing cavity simulation space, and the oil return pool construction block is provided with a circulation hole communicated with the oil return simulation pool and the oil return port; the front cover plate and the rear cover plate are connected to the front side and the rear side of the shell and clamp the oil return pool construction block. The bearing simulation rotating disc is arranged in the bearing cavity simulation space, and the connection driving rotating shaft penetrates through the rear cover plate.

Description

Technical Field

[0001] This application belongs to the field of aero-engine bearing cavity testing technology, specifically relating to an aero-engine bearing cavity tester, its testing system, and testing method. Background Technology

[0002] The bearing cavity is a crucial component of the aero-engine lubrication system. The interior of the bearing cavity is a complex two-phase oil-gas flow environment. During the bearing cavity design process, simply using simulation software to analyze the flow characteristics of the bearing cavity is insufficient to accurately simulate the actual conditions within it. This can easily lead to problems such as poor oil return, oil leakage, and excessive cavity pressure during the early stages of aero-engine development. Therefore, it is necessary to design an aero-engine bearing cavity testing device to conduct bearing cavity testing research.

[0003] The oil return sump is a key structure that affects the oil return flow characteristics of the bearing cavity in aero-engines. Structural parameters such as the size of the oil return sump, the direction of the oil return sump outlet, and the obstruction of the oil return sump inlet all affect the oil return efficiency of the bearing cavity.

[0004] Currently, aero-engine bearing cavity testers are all based on the typical aero-engine bearing cavity structure design, simulating the oil supply, air intake, ventilation, and oil return systems to study the internal flow of the bearing cavity. However, they neglect the experimental study of the oil return pool, which cannot effectively evaluate the oil return efficiency of the bearing cavity and makes it difficult to effectively guide the design of aero-engine lubrication systems.

[0005] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0006] The purpose of this application is to provide an aero-engine bearing cavity tester and its test system and test method to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An aero-engine bearing cavity tester includes a housing, an oil return sump block, a front cover plate, a rear cover plate, a bearing simulation turntable, and a drive shaft.

[0009] The shell is rectangular, and inside it forms a bearing cavity simulation space and an oil return pool structure space connected to the bearing cavity simulation space. The bearing cavity simulation space is circular, and the oil return pool structure space is rectangular. The oil return pool structure space is located below the bearing cavity simulation space, and the bearing cavity simulation space and the oil return pool structure space are open on the front and rear sides of the shell.

[0010] The side wall of the housing has an oil supply port, a ventilation port, an air inlet, and a pressure measuring hole that communicate with the simulated space of the bearing cavity. The oil supply port and the ventilation port are located at the top of the housing, while the air inlet and the pressure measuring hole are located on the left and right sides of the housing. The pressure measuring hole is used to install a pressure gauge.

[0011] The shell sidewall has an oil return port that communicates with the oil return pool structure space, and the oil return port is located at the bottom of the shell;

[0012] The oil return pool structure block is set in the oil return pool structure space, forming an oil return simulation pool with the bearing cavity simulation space. The oil return pool structure block has a flow hole that connects the oil return simulation pool and the oil return port.

[0013] The front and rear cover plates are connected to the front and rear sides of the shell, clamping the oil return pool structural block;

[0014] The bearing simulation turntable is set in the bearing cavity simulation space, and the connecting drive shaft is set through the rear cover plate.

[0015] Optionally, in the aforementioned aero-engine bearing cavity tester, the front cover plate and the rear cover plate are bolted to the front and rear sides of the housing.

[0016] Optionally, in the aforementioned aero-engine bearing cavity tester, the front cover is made of a transparent material.

[0017] An aero-engine bearing cavity testing system includes the aforementioned aero-engine bearing cavity tester, a turntable drive motor, a turntable drive frequency converter cabinet, and an air supply system, an oil supply system, a ventilation system, and an oil return system.

[0018] The turntable drive motor is connected to the drive shaft, and the turntable drive frequency converter cabinet is connected to the turntable drive motor.

[0019] The gas supply system includes gas supply pipelines;

[0020] The gas supply pipeline is connected to an air compressor at the inlet and to an air inlet at the outlet. A pressure stabilizing tank, a first valve, a first pressure sensor, a first gas flow meter, and a second valve are installed on it in sequence.

[0021] The fuel supply system includes fuel supply pipelines;

[0022] The inlet of the oil supply pipeline is connected to the lubricating oil tank, and the outlet is connected to the oil supply port. The pipeline is equipped with a fifth valve, an oil supply pump, a third valve, a liquid flow meter, a sixth valve, and a second pressure sensor in sequence. The oil supply pump is connected to the oil supply pump motor, and the oil supply pump frequency converter cabinet is connected to the oil supply pump motor.

[0023] The ventilation system includes ventilation ducts;

[0024] The ventilation duct is connected to a ventilation port, on which an oil-gas separator, a third pressure sensor, a second gas flow meter, and a seventh valve are installed in sequence.

[0025] The oil return system includes oil return lines and exhaust branches;

[0026] The inlet of the return oil pipeline is connected to the return oil port, and the outlet is connected to the oil storage tank set on the weighing module. The tank is equipped with the eighth valve, the tenth valve, the fourth pressure sensor, the return oil pump, the fifth pressure sensor, the twelfth valve, the second oil-gas separator, and the fourteenth valve in sequence.

[0027] A return oil pump motor is connected to the return oil pump, and a return oil pump frequency converter is connected to the return oil pump motor.

[0028] The exhaust branch inlet is connected to the second oil-gas separator, which is equipped with the thirteenth valve and the third gas flow meter in sequence.

[0029] Optionally, in the above-mentioned aero-engine bearing cavity test system, the oil supply system also includes an oil supply branch;

[0030] The oil supply branch inlet connects to the oil supply pipeline, and the outlet connects to the lubricating oil tank. A fourth valve is installed on it. The inlet of the oil supply branch is located between the liquid flow meter and the sixth valve.

[0031] Optionally, in the above-mentioned aero-engine bearing cavity test system, the outlet of the ventilation duct is connected to the first oil-gas separator.

[0032] Optionally, in the above-mentioned aero-engine bearing cavity test system, the oil return system also includes a front oil drain branch and a rear oil drain branch;

[0033] The inlet of the front oil branch line is connected to the return oil line, and a ninth valve is installed on it. The inlet of the front oil branch line is located between the eighth and tenth valves.

[0034] The rear oil branch inlet is connected to the return oil pipeline, and an eleventh valve is installed on it. The front oil branch inlet is located between the fifth pressure sensor and the twelfth valve.

[0035] A test method for an aero-engine bearing cavity, implemented based on the aforementioned aero-engine bearing cavity test system, includes:

[0036] Steps for measuring the oil-gas ratio at the ventilation outlet:

[0037] Start the bearing cavity motor. After the speed stabilizes, start the oil supply pump motor. Adjust the speed of the oil supply pump motor and the opening of the third and sixth valves to achieve the target oil supply flow rate. Open the eighth, tenth, twelfth, thirteenth, fourteenth, and seventh valves. Start the return oil pump motor and adjust its speed to the target value. Start the air compressor to supply air to the simulated space of the bearing cavity. Adjust the opening of the first and second valves to achieve the target air supply flow rate. After the system stabilizes, read the gas flow rate in the ventilation pipeline through the second gas flow meter, and weigh the lubricating oil in the oil-gas separator after 1 minute. Then, calculate the oil-gas ratio at the ventilation outlet.

[0038] Optionally, the above-mentioned test method for aero-engine bearing cavities may further include:

[0039] Steps for measuring the oil-gas ratio at the return oil outlet:

[0040] Start the bearing cavity motor. After the speed stabilizes, start the oil supply pump motor. Adjust the speed of the oil supply pump motor and the opening of the third and sixth valves to make the oil supply flow reach the target value. Open the eighth, tenth, twelfth, thirteenth and fourteenth valves. Start the return oil pump motor and adjust the speed of the return oil pump motor to the target value. Start the air compressor to supply air to the simulated space of the bearing cavity. Adjust the opening of the first and second valves to make the air supply flow reach the target value. After the system runs stably, read the gas flow in the exhaust branch through the third gas flow meter, and weigh the mass of lubricating oil in the oil storage tank after running for 1 minute. Then calculate the oil-gas ratio at the return oil outlet.

[0041] Optionally, the above-mentioned test method for the bearing cavity of an aero-engine further includes: in the steps of measuring the oil-gas ratio at the ventilation outlet and the oil-gas ratio at the return oil outlet, using a high-speed camera to collect and observe the flow field distribution in the simulated space of the bearing cavity and the height of the accumulated oil level in the simulated return oil pool, so as to obtain the flow field distribution and the height of the accumulated oil level inside the bearing cavity. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of the aero-engine bearing cavity test apparatus provided in the embodiments of this application;

[0043] Figure 2 This is a schematic diagram of the oil return tank construction block provided in the embodiment of this application being set in the oil return tank construction space to construct oil return tank simulation tanks with different structures;

[0044] Figure 3 This is a schematic diagram of the aero-engine bearing cavity testing system provided in the embodiments of this application;

[0045] Figure 4 These are images of the flow field distribution in the simulated space of the bearing cavity and the oil level in the simulated oil return pool, provided in the embodiments of this application.

[0046] in:

[0047] 1-Air compressor; 2-Pressure tank; 3-First valve; 4-First pressure sensor; 5-First gas flow meter; 6-Second valve;

[0048] 7-Inverter cabinet for oil supply pump; 8-Oil supply pump motor; 9-Oil supply pump; 10-Third valve; 11-Liquid flow meter; 12-Fourth valve; 13-Lubricating oil tank; 14-Fifth valve; 15-Sixth valve; 16-Second pressure sensor;

[0049] 18-Bearing cavity motor; 19-Bearing frequency converter cabinet;

[0050] 20-Oil-gas separator; 21-Third pressure sensor; 22-Second gas flow meter; 23-Seventh valve; 24-First oil-gas separator box;

[0051] 25-Eighth valve; 26-Ninth valve; 27-Tenth valve; 28-Fourth pressure sensor; 29-Return oil pump; 30-Return oil pump motor; 31-Return oil pump frequency converter; 32-Fifth pressure sensor; 33-Eleventh valve; 34-Twelfth valve; 35-Second oil-gas separator; 36-Thirteenth valve; 37-Third gas flow meter; 38-Fourteenth valve; 39-Weighing module;

[0052] 40 - Shell; 41 - Oil return tank structural block; 42 - Front cover plate; 43 - Rear cover plate; 44 - Bearing simulation turntable; 45 - Drive shaft;

[0053] A-Oil supply port; B-Ventilation port; C-Air inlet; D-Pressure test port; E-Oil return port.

[0054] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0055] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0056] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0057] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0058] Since the return oil pool is a key structure affecting the return oil flow characteristics of the bearing cavity of an aero-engine, and the evaluation scheme for the return oil efficiency of the bearing cavity includes the internal flow field distribution of the bearing cavity, the height of the accumulated oil level, the oil-gas ratio at the ventilation outlet, and the oil-gas ratio at the return oil outlet, this application provides an aero-engine bearing cavity tester and its test system and test method.

[0059] Aero-engine bearing cavity tester, such as Figure 1 As shown, it includes a housing 40, an oil return pool structure block 41, a front cover plate 42, a rear cover plate 43, a bearing simulation turntable 44, and a drive shaft 45.

[0060] The shell 40 is rectangular, and inside it forms a bearing cavity simulation space and an oil return pool structure space connected to the bearing cavity simulation space. The bearing cavity simulation space is circular, and the oil return pool structure space is rectangular. The oil return pool structure space is located below the bearing cavity simulation space, and the bearing cavity simulation space and the oil return pool structure space are open on the front and rear sides of the shell 40.

[0061] The side wall of the housing 40 has an oil supply port A, a vent B, an air inlet C, and a pressure measuring hole D that communicate with the bearing cavity simulation space. The oil supply port A and the vent B are located at the top of the housing 40, and the air inlet C and the pressure measuring hole D are located on the left and right sides of the housing 40. The pressure measuring hole D is used to install a pressure gauge to measure the pressure in the bearing cavity simulation space.

[0062] The shell 40 has an oil return port E on its side wall that communicates with the oil return pool structure space. The oil return port E is located at the bottom of the shell 40.

[0063] The oil return pool structure block 41 is set in the oil return pool structure space, forming an oil return simulation pool with the bearing cavity simulation space. The oil return pool structure block 41 has a flow hole that connects the oil return simulation pool and the oil return port E.

[0064] The oil return tank construction block 41 is detachable and can be designed according to needs, based on structural parameters such as the size of the oil return tank, the direction of the oil return tank outlet, and the obstruction of the oil return tank inlet. This allows for the construction of oil return simulation tanks with different structures within the oil return tank construction space, such as cylindrical oil return pipe-shaped, oil return trough-shaped, wedge-shaped trough-shaped with obstruction, and axial outlet oil return simulation tanks. Figure 2 As shown, this allows for convenient verification of the influence of different oil return pool structures on the oil return flow characteristics of aero-engine bearing cavities.

[0065] The front cover plate 42 and the rear cover plate 43 are connected to the front and rear sides of the housing 40, specifically by bolts, to clamp the oil return pool structure block, and the front cover plate 42 is made of transparent material.

[0066] The bearing simulation turntable 44 is set in the bearing cavity simulation space, and the drive shaft 45 is set through the rear cover plate 43.

[0067] Based on the above example of the aircraft engine bearing cavity tester, an aircraft engine bearing cavity test system has been further designed, such as... Figure 3 As shown, it includes a turntable drive motor 18, a turntable drive frequency converter cabinet 19, and an air supply system, an oil supply system, a ventilation system, and an oil return system.

[0068] The turntable drive motor 18 is connected to the drive shaft 45, and the turntable drive frequency converter cabinet 19 is connected to the turntable drive motor 18. The turntable drive frequency converter cabinet 19 can control the output power of the turntable drive motor 18 and drive the bearing through the drive shaft 45 to simulate the rotation of the turntable 44.

[0069] The gas supply system includes gas supply pipelines.

[0070] The gas supply pipeline is connected to the air compressor 1 at the inlet and to the air inlet C at the outlet. A pressure stabilizing tank 2, a first valve 3, a first pressure sensor 4, a first gas flow meter 5, and a second valve 6 are installed on it in sequence.

[0071] The air supply system uses an air compressor 1 to pressurize air into a pressure stabilizing tank 2. After the pressure stabilizes, the air is introduced into the bearing cavity simulation space to simulate high pressure entering the bearing cavity.

[0072] The oil supply system includes oil supply pipelines and oil supply branches.

[0073] The oil supply pipeline is connected to the lubricating oil tank 13 at the inlet and to the oil supply port A at the outlet. It is equipped with a fifth valve 14, an oil supply pump 9, a third valve 10, a liquid flow meter 11, a sixth valve 15, and a second pressure sensor 16 in sequence. The oil supply pump 9 is connected to the oil supply pump motor 8, and the oil supply pump motor 8 is connected to the oil supply pump frequency converter cabinet 7. The oil supply pump frequency converter cabinet 7 can control the output power of the oil supply pump motor 8 and drive the oil supply pump 9 to rotate.

[0074] The inlet of the oil supply branch is connected to the oil supply pipeline, and the outlet is connected to the lubricating oil tank 13, which is equipped with a fourth valve 12. The inlet of the oil supply branch is located between the liquid flow meter 11 and the sixth valve 15, and is used for the overflow of the oil supply pump 9 to regulate the oil supply flow.

[0075] The oil supply system stores lubricating oil in the oil tank 13 and uses the oil supply pump 9 to deliver the lubricating oil to the bearing cavity simulation space. The oil supply flow rate is regulated by the valve on the pipeline between the oil supply pump 9 and the bearing cavity simulation space to simulate the entry of lubricating oil into the bearing cavity.

[0076] The ventilation system includes ventilation ducts.

[0077] The inlet of the ventilation duct is connected to the ventilation port B, and the outlet is connected to the first oil-gas separator 24, which is equipped with an oil-gas separator 20, a third pressure sensor 21, a second gas flow meter 22, and a seventh valve 23 in sequence.

[0078] The ventilation system connects the bearing cavity simulation space to the atmosphere, and the gas and a small amount of lubricating oil escaping from the bearing cavity simulation space are separated into gas and liquid in the oil-gas separator 20.

[0079] The oil return system includes an oil return line, a front oil drain branch, a rear oil drain branch, and an exhaust branch.

[0080] The inlet of the return oil pipeline is connected to the return oil port E, and the outlet is connected to the oil storage tank set on the weighing module 39. The tank is equipped with the eighth valve 25, the tenth valve 27, the fourth pressure sensor 28, the return oil pump 29, the fifth pressure sensor 32, the twelfth valve 34, the second oil-gas separator 35, and the fourteenth valve 38 in sequence.

[0081] A return oil pump motor 30 is connected to the return oil pump 29, and a return oil pump frequency converter 31 is connected to the return oil pump motor 30. The return oil pump frequency converter 31 can control the output power of the return oil pump motor 30 and drive the return oil pump 29 to rotate.

[0082] The inlet of the front oil branch connects to the return oil line, and a ninth valve 26 is installed on it. The inlet of the front oil branch is located between the eighth valve 25 and the tenth valve 27, and is used to measure the oil volume in the simulated space of the bearing cavity after the test.

[0083] The rear oil branch inlet is connected to the return oil pipeline, and an eleventh valve 33 is installed on it. The front oil branch inlet is located between the fifth pressure sensor 32 and the twelfth valve 34. This is used to empty the lubricating oil accumulated in the bearing cavity by the return oil pump 29 after the test.

[0084] The exhaust branch inlet is connected to the second oil-gas separator 35, which is equipped with a thirteenth valve 36 and a third gas flow meter 37 to measure the air content in the return oil.

[0085] In the oil return system, the oil-gas mixture is extracted from the bearing cavity simulation space by the oil return pump 29 and transported to the second oil-gas separator 35. Oil-gas separation is completed in the second oil-gas separator 35, and the flow rate of the separated air is monitored by the third gas flow meter 37.

[0086] Based on the aero-engine bearing cavity test system disclosed in the above embodiments, bearing cavity tests are conducted to determine the bearing cavity oil return efficiency, which can be performed by referring to the following steps:

[0087] Steps for measuring the oil-gas ratio at the ventilation outlet:

[0088] Start the bearing cavity motor 18. After the speed stabilizes, start the oil supply pump motor 8. Adjust the speed of the oil supply pump motor 8 and the opening of the third valve 10 and the sixth valve 15 to supply oil to the simulated space of the bearing cavity, so that the oil supply flow reaches the target value. Keep the fourth valve 12, the ninth valve 26, and the eleventh valve 33 closed, that is, close the overflow of oil supply and return. Open the eighth valve 25, the tenth valve 27, the twelfth valve 34, the thirteenth valve 36, the fourteenth valve 38, and the seventh valve 23. Start the return oil pump motor 30 and adjust... When the return oil pump motor 30 reaches the target speed, the flow rate of the return oil pipeline reaches the required level. Then, the air compressor 1 is started to supply air to the simulated space of the bearing cavity. The opening of the first valve 3 and the second valve 6 is adjusted to make the air supply flow rate reach the target value. After the system is running stably, the oil-gas mixture passes through the oil-gas separator 20, and the lubricating oil remains in the oil-gas separator 20. Subsequently, the gas flow rate in the ventilation pipeline can be read by the second gas flow meter 22, and the mass of the lubricating oil in the oil-gas separator 20 can be weighed after running for 1 minute. Then, the oil-gas ratio at the ventilation outlet can be calculated.

[0089] Steps for measuring the oil-gas ratio at the return oil outlet: Start the bearing cavity motor 18. After the speed stabilizes, start the oil supply pump motor 8. Adjust the speed of the oil supply pump motor 8 and the opening of the third valve 10 and the sixth valve 15 to supply oil to the simulated space of the bearing cavity, so that the oil supply flow reaches the target value. Keep the fourth valve 12, the ninth valve 26, and the eleventh valve 33 closed, that is, close the overflow of oil supply and return. Open the eighth valve 25, the tenth valve 27, the twelfth valve 34, the thirteenth valve 36, and the fourteenth valve 38. Start the return oil pump motor 30 and adjust the speed of the return oil pump motor 30 to the target value. Once the return oil pipeline flow rate reaches the required level, the air compressor 1 is started to supply air to the simulated space of the bearing cavity. The opening of the first valve 3 and the second valve 6 is adjusted to make the air supply flow rate reach the target value. After the system runs stably, the oil-gas mixture passes through the second oil-gas separator 35, and the lubricating oil is discharged into the oil storage tank set on the weighing module 39. The gas is discharged through the exhaust branch. Subsequently, the gas flow rate in the exhaust branch can be read by the third gas flow meter 37, and the mass of the lubricating oil in the oil storage tank can be weighed by the weighing module 39 after running for 1 minute. Then, the oil-gas ratio at the return oil outlet can be calculated.

[0091] In the steps of measuring the oil-gas ratio at the ventilation outlet and the oil-gas ratio at the return oil outlet, a high-speed camera is used to collect and observe the flow field distribution in the simulated space of the bearing cavity and the oil level in the simulated return oil pool. The flow field distribution and oil level inside the bearing cavity are obtained, and the return oil efficiency of the bearing cavity is analyzed.

[0092] In a specific example, a high-speed camera is used to acquire and observe images of the flow field distribution within the simulated bearing cavity and the oil level height within the simulated return oil pool, such as... Figure 4 As shown.

[0093] The aero-engine bearing cavity tester, its test system, and test method disclosed in the above embodiments are designed with a modular, detachable structure. This allows for convenient design of the oil return simulation pool structure as needed, facilitating the testing of the influence of the oil pool structure parameters on the oil return flow characteristics of the bearing cavity. Simultaneously, a high-speed camera is used to collect and observe the internal flow field distribution and oil level height of the bearing cavity. Oil-gas separators are installed in the ventilation and oil return systems to separate oil and gas, and the oil volume and gas flow rate are tested to obtain the oil-gas ratio at the ventilation outlet and oil return outlet. This enables the evaluation of the bearing cavity oil return efficiency and effectively guides the design of the aero-engine lubrication system.

[0094] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A test apparatus for an aero-engine bearing cavity, characterized in that, Includes housing (40), oil return pool structure block (41), front cover plate (42), rear cover plate (43), bearing simulation turntable (44), and drive shaft (45). The shell (40) is rectangular, and a bearing cavity simulation space and an oil return pool structure space connected to the bearing cavity simulation space are formed therein. The bearing cavity simulation space is circular, the oil return pool structure space is rectangular, and the oil return pool structure space is located below the bearing cavity simulation space. The bearing cavity simulation space and the oil return pool structure space are open on the front and rear sides of the shell (40). The side wall of the housing (40) has an oil supply port (A), a ventilation port (B), an air inlet (C), and a pressure measuring hole (D) that are connected to the simulated space of the bearing cavity. The oil supply port (A) and the ventilation port (B) are located at the top of the housing (40), and the air inlet (C) and the pressure measuring hole (D) are located on the left and right sides of the housing (40). The pressure measuring hole (D) is used to install a pressure gauge. The shell (40) has an oil return port (E) on its side wall that communicates with the oil return pool structure space. The oil return port (E) is located at the bottom of the shell (40). The oil return pool structure block (41) is set in the oil return pool structure space, forming an oil return simulation pool with the bearing cavity simulation space. The oil return pool structure block (41) has a flow hole that connects the oil return simulation pool and the oil return port (E). The front cover plate (42) and the rear cover plate (43) are connected to the front and rear sides of the housing (40) and clamp the oil return pool structure block; The bearing simulation turntable (44) is set in the bearing cavity simulation space, and the drive shaft (45) is set through the rear cover plate (43).

2. The aero-engine bearing cavity test apparatus according to claim 1, characterized in that, The front cover plate (42) and the rear cover plate (43) are bolted to the front and rear sides of the housing (40).

3. The aero-engine bearing cavity test apparatus according to claim 2, characterized in that, The front cover (42) is made of transparent material.

4. A test system for an aero-engine bearing cavity, characterized in that, Includes the aircraft engine bearing cavity tester as described in claim 3, the turntable drive motor (18), the turntable drive frequency converter (19), and the air supply system, oil supply system, ventilation system, and oil return system; The turntable drive motor (18) is connected to the drive shaft (45), and the turntable drive frequency converter cabinet (19) is connected to the turntable drive motor (18). The gas supply system includes gas supply pipelines; The gas supply pipeline is connected to an air compressor (1) at the inlet and to an air inlet (C) at the outlet. A pressure stabilizing tank (2), a first valve (3), a first pressure sensor (4), a first gas flow meter (5), and a second valve (6) are installed on it in sequence. The fuel supply system includes fuel supply pipelines; The inlet of the oil supply pipeline is connected to the lubricating oil tank (13), and the outlet is connected to the oil supply port (A). The fifth valve (14), the oil supply pump (9), the third valve (10), the liquid flow meter (11), the sixth valve (15), and the second pressure sensor (16) are installed on it in sequence. The oil supply pump (9) is connected to the oil supply pump motor (8), and the oil supply pump motor (8) is connected to the oil supply pump frequency converter cabinet (7). The ventilation system includes ventilation ducts; The ventilation duct is connected to the ventilation port (B), on which an oil-gas separator (20), a third pressure sensor (21), a second gas flow meter (22), and a seventh valve (23) are installed in sequence. The oil return system includes oil return lines and exhaust branches; The inlet of the return oil pipeline is connected to the return oil port (E), and the outlet is connected to the oil storage tank set on the weighing module (39). The tank is equipped with the eighth valve (25), the tenth valve (27), the fourth pressure sensor (28), the return oil pump (29), the fifth pressure sensor (32), the twelfth valve (34), the second oil-gas separator (35), and the fourteenth valve (38) in sequence. A return oil pump motor (30) is connected to the return oil pump (29), and a return oil pump frequency converter (31) is connected to the return oil pump motor (30). The exhaust branch inlet is connected to the second oil-gas separator (35), which is equipped with the thirteenth valve (36) and the third gas flow meter (37) in sequence.

5. The aero-engine bearing cavity testing system according to claim 4, characterized in that, The fuel supply system also includes fuel supply branches; The oil supply branch inlet is connected to the oil supply pipeline, and the outlet is connected to the lubricating oil tank (13), which is equipped with a fourth valve (12). The inlet of the oil supply branch is located between the liquid flow meter (11) and the sixth valve (15).

6. The aero-engine bearing cavity testing system according to claim 5, characterized in that, The outlet of the ventilation duct is connected to the first oil-gas separator (24).

7. The aero-engine bearing cavity testing system according to claim 6, characterized in that, The oil return system also includes a front oil drain branch and a rear oil drain branch; The inlet of the front oil branch is connected to the return oil pipeline, and a ninth valve (26) is installed on it. The inlet of the front oil branch is located between the eighth valve (25) and the tenth valve (27). The inlet of the rear oil branch is connected to the return oil pipeline, and an eleventh valve (33) is installed on it. The inlet of the front oil branch is located between the fifth pressure sensor (32) and the twelfth valve (34).

8. A test method for an aero-engine bearing cavity, implemented based on the aero-engine bearing cavity test system of claim 7, characterized in that, include: Steps for measuring the oil-gas ratio at the ventilation outlet: Start the bearing cavity motor (18), and after the speed stabilizes, start the oil supply pump motor (8). Adjust the speed of the oil supply pump motor (8) and the opening of the third valve (10) and the sixth valve (15) to make the oil supply flow reach the target value. Open the eighth valve (25), the tenth valve (27), the twelfth valve (34), the thirteenth valve (36), the fourteenth valve (38), and the seventh valve (23). Start the return oil pump motor (30), adjust the speed of the return oil pump motor (30) to the target value, start the air compressor (1) to supply air to the bearing cavity simulation space, adjust the opening of the first valve (3) and the second valve (6) to make the air supply flow reach the target value. After the system runs stably, read the gas flow in the ventilation pipeline through the second gas flow meter (22), and weigh the lubricating oil in the oil-gas separator (20) after 1 minute, and then calculate the oil-gas ratio at the ventilation outlet.

9. The test method for the bearing cavity of an aero-engine according to claim 8, characterized in that, Also includes: Steps for measuring the oil-gas ratio at the return oil outlet: Start the bearing cavity motor (18), and after the speed stabilizes, start the oil supply pump motor (8). Adjust the speed of the oil supply pump motor (8) and the opening of the third valve (10) and the sixth valve (15) to make the oil supply flow reach the target value. Open the eighth valve (25), the tenth valve (27), the twelfth valve (34), the thirteenth valve (36), and the fourteenth valve (38). Start the return oil pump motor (30), adjust the speed of the return oil pump motor (30) to the target value, start the air compressor (1) to supply air to the bearing cavity simulation space, adjust the opening of the first valve (3) and the second valve (6) to make the air supply flow reach the target value. After the system runs stably, read the gas flow in the exhaust branch through the third gas flow meter (37), and weigh the mass of lubricating oil in the oil storage tank with the weighing module (39) after running for 1 minute, and then calculate the oil-gas ratio at the return oil outlet.

10. The test method for the bearing cavity of an aero-engine according to claim 9, characterized in that, Also includes: In the steps of measuring the oil-gas ratio at the ventilation outlet and the oil-gas ratio at the return oil outlet, a high-speed camera is used to collect and observe the flow field distribution in the simulated space of the bearing cavity and the height of the oil level in the simulated oil return pool, so as to obtain the flow field distribution and the height of the oil level inside the bearing cavity.

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