Aviation bearing test tool
By designing a test fixture for aerospace bearings, and using a multi-hole ring under-lubrication path and a test bearing to simulate the high-speed and high-load conditions of aerospace bearings, the problem of poor performance of traditional lubrication methods was solved, and the uniformity of lubrication and the reliability of test data were achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-27
- Publication Date
- 2026-04-07
AI Technical Summary
Traditional bearing oil lubrication methods are ineffective in the high-speed, high-load environment of aero-engine main shaft bearings. Existing test equipment cannot effectively simulate actual working conditions, leading to insufficient lubrication and wear and heat generation problems.
An aerospace bearing test fixture was designed, including a housing, a drive assembly, and a loading assembly. Multiple oil injection holes and connecting holes form a lubrication path under the ring. Combined with centrifugal force and vibration, it simulates the lubrication conditions of the bearing under actual working conditions. It is equipped with a test bearing and an oil guide ring to evenly distribute the lubricating oil and monitor temperature and vibration data.
It enables precise lubrication of aerospace bearings under high speed and high load conditions, improves the stability of the test and the reliability of the data, avoids wear and heat caused by insufficient local lubrication, and can monitor the lubrication status and vibration response in real time.
Smart Images
Figure CN224095392U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to bearing test tool field especially an aviation bearing test tool. BACKGROUND
[0002] The aviation bearing refers to the special bearing applied to the aviation equipment, and is usually the main shaft bearing of the aviation engine. The engine is the core component of the aircraft power system, and its reliability is crucial to flight safety. The bearing needs to face the environment of high speed and high load, and also has the particularity of the bearing design itself. The operation stability is more demanding, and the oil supply lubrication is very important. The traditional bearing oil lubrication is usually through side spray oil supply or through the oil supply hole designed on the bearing outer ring to lubricate the bearing. The method has mature technology in low speed or small bearing and ordinary working condition environment. However, for the aviation engine main shaft bearing with special working condition, the practice proves that the lubricating effect is not good. At present, in the actual working condition of the aviation engine bearing, the oil supply method of the ring under lubrication has better advantages for the lubricating effect of the bearing, and is more applied in the industry. Therefore, a test device more suitable for the actual working condition is set to verify whether the bearing performance developed meets the design requirements, and sufficient data is collected through the test to facilitate subsequent optimization and improvement. SUMMARY
[0003] In view of the defects of the prior art, the utility model provides an aviation bearing test tool more suitable for the actual working condition.
[0004] In order to achieve the above purpose, the utility model provides an aviation bearing test tool, which comprises a shell, a driving assembly and a loading assembly. The shell comprises a cover plate, an axial through slot, a first oil injection hole and a first oil injection rod arranged at the position corresponding to the first oil injection hole. The driving assembly comprises a driving shaft. The driving shaft is arranged in the through slot and forms two installation positions for the bearing to be tested between the driving shaft and the shell. The driving shaft comprises a hollow inner cavity and a plurality of radial first communication holes. The first communication holes communicate the inner cavity and the inner side of the shell. The loading assembly comprises an axial loading part. The axial loading part comprises an outer ring part and a shaft part. The outer ring part and the cover plate are arranged on the two sides of the shell in the axial direction respectively. The outer ring part and the cover plate can be axially abutted with the outer ring of the bearing to be tested in the adjacent installation position respectively. The outer ring part covers the inner side of the first oil injection hole and is provided with a second communication hole. The shaft part is arranged in the inner cavity and is provided with a third communication hole and an oil groove. The second communication hole communicates with the oil groove. The third communication hole communicates the oil groove and the inner cavity.
[0005] The advantages of the above technical solution are: the dual mounting positions formed by the drive shaft and the housing provide space for the two bearings to be tested. Combined with the axial loading component's outer ring and cover plate, which axially abut against the outer rings of the bearings on both sides, the operating state of the aircraft bearing under axial load can be accurately simulated. Furthermore, a through groove, a first oil injection hole, and a first oil injection rod are provided. A second connecting hole, a third connecting hole, and an oil groove are respectively provided on the outer ring and shaft. Lubricating oil is injected through the first oil injection rod from the first oil injection hole, flows into the shaft's oil groove through the second connecting hole of the outer ring, and then through the third connecting hole and the drive shaft's inner cavity and the first connecting hole. Through centrifugal force and vibration during operation, lubrication of the area under the bearing ring is achieved, ensuring that the test conditions closely resemble the actual oil supply conditions during operation.
[0006] The present invention can be further configured as follows: the housing is provided with a second oil injection hole and a second oil injection rod corresponding to the second oil injection hole; the first oil injection hole and the second oil injection hole are respectively provided on both sides of the housing axial direction; the cover plate covers the inner side of the second oil injection hole and is provided with a fourth connecting hole; the outer ring is provided with a side hole connecting to the second connecting hole; the fourth connecting hole and the side hole are respectively connected to two mounting positions.
[0007] By further designing the housing, a second oil injection hole and a second oil injection rod are provided on the housing, with the first and second oil injection holes respectively located on both sides of the housing axial direction. A fourth connecting hole and a side hole are then provided on the cover plate and the outer ring, connecting the fourth connecting hole and the side hole to the two mounting positions respectively, thus better lubricating the two bearings to be tested.
[0008] The present invention can be further configured such that: a third oil injection hole and a third oil injection rod corresponding to the third oil injection hole are provided in the middle of the housing, and a test bearing is provided between the housing and the drive shaft at the location corresponding to the third oil injection hole.
[0009] By further configuring the test bearing, the complex load transfer and interaction of multi-stage bearings in aviation equipment can be better simulated, closely matching actual operating conditions. The lubrication of the test bearing can be enhanced by using the third oil injection hole and the third oil injection rod.
[0010] The present invention can be further configured such that: there are two test bearings, and an oil guide ring is provided between the two test bearings. The oil guide ring covers the bottom of the third oil injection hole, and the oil guide ring is provided with a fourth connecting hole, which connects the third oil injection hole and the two sides of the guide ring along the axial direction.
[0011] By further configuring the two test bearings to work together, the complex load transfer and interaction of multi-stage bearings in aviation equipment can be simulated more accurately, closely matching actual operating conditions. The oil guide ring covers the third oil injection hole, and its fourth connecting hole evenly distributes lubricating oil to the two test bearings on both sides, ensuring that the area of the two test bearings and the surrounding test bearings can be adequately lubricated, forming a continuous lubrication path under the ring. This avoids wear and heat caused by insufficient local lubrication, effectively improving the operating stability of the bearings in the simulation test and the reliability of the test data.
[0012] The present invention can be further configured such that the loading component includes a radial loading rod, which is connected to the middle part of the housing.
[0013] With further configuration, the radial loading rod can precisely apply radial loads of different sizes and directions. In conjunction with the axial loading component, it can simulate the complex stress conditions such as centrifugal force and airflow impact that aerospace bearings experience in actual operation, making the test environment more closely resemble real working conditions.
[0014] This utility model can be further configured such that: the housing is provided with temperature measuring holes for inserting thermometers at two corresponding mounting positions.
[0015] By further configuring the thermometer to be directly inserted into the temperature measuring hole, the temperature change of the bearing under test can be monitored in real time and accurately during operation. Temperature is a key indicator reflecting the bearing's lubrication status, wear degree, and adaptability to operating conditions. This design can promptly detect abnormal temperature rises caused by factors such as insufficient lubrication and abnormal load.
[0016] The present invention can be further configured such that: detection holes are provided on both sides of the housing corresponding to the axial direction of the third oil injection hole.
[0017] By further configuring the system, detection holes are set on both sides of the third oil injection hole along the axial direction, allowing the installation of vibration measurement rods. This enables the real-time capture of bearing vibration data during loading and lubrication. Combined with the complex working condition simulation constructed by the central double-test bearing and the radial loading rod, the vibration response characteristics of the bearing under different loads and lubrication conditions can be effectively analyzed. Attached Figure Description
[0018] Figure 1 This is a schematic diagram of the structure of an embodiment of the present utility model. Figure 1 ;
[0019] Figure 2 This is a schematic diagram of the structure of an embodiment of the present utility model. Figure 2 ;
[0020] Figure 3 This is an embodiment of the present utility model. Figure 2 Sectional view at point AA;
[0021] Figure 4 This is a schematic diagram of the drive shaft structure in an embodiment of the present invention;
[0022] Figure 5 This is a schematic diagram of the axial loading component in an embodiment of this utility model;
[0023] Figure 6 This is a schematic diagram of the oil guide ring in an embodiment of the present invention;
[0024] The components include: housing 1; cover plate 11; through groove 12; first oil injection hole 13; first oil injection rod 14; second oil injection hole 15; second oil injection rod 16; third oil injection hole 17; third oil injection rod 18; temperature measuring hole 19; detection hole 10; drive assembly 2; drive shaft 21; inner cavity 211; first connecting hole 212; loading assembly 3; axial loading component 31; outer ring 311; shaft 312; second connecting hole 313; third connecting hole 314; oil groove 315; side hole 316; radial loading rod 32; mounting position 4; test bearing 5; oil guide ring 6; fourth connecting hole 61. Detailed Implementation
[0025] An example of the implementation of this utility model of an aircraft bearing testing fixture Figures 1-6 As shown: The system includes a housing 1, a drive assembly 2, and a loading assembly 3. The housing 1 includes a cover plate 11, an axially penetrating through groove 12, a first oil injection hole 13, and a first oil injection rod 14 corresponding to the position of the first oil injection hole 13. The drive assembly 2 includes a drive shaft 21, which passes through the through groove 12 and forms two mounting positions 4 between itself and the housing 1 for mounting the bearing to be tested. The drive shaft 21 includes a hollow inner cavity 211 and several radially extending first connecting holes 212, which connect the inner cavity 211 and the inner side of the housing 1. The loading assembly 3 includes an axially... The loading member 31 includes an outer ring portion 311 and a shaft portion 312. The outer ring portion 311 and the cover plate 11 are respectively disposed on both sides of the housing 1 in the axial direction, and the outer ring portion 311 and the cover plate 11 can respectively abut against the outer ring of the bearing to be tested at the adjacent mounting position 4 in the axial direction. The outer ring portion 311 covers the inner side of the first oil injection hole 13 and is provided with a second connecting hole 313. The shaft portion 312 passes through the inner cavity 211 and is provided with a third connecting hole 314 and an oil groove 315. The second connecting hole 313 connects to the oil groove 315, and the third connecting hole 314 constitutes the connection between the oil groove 315 and the inner cavity 211.
[0026] The housing 1 is provided with a second oil injection hole 15 and a second oil injection rod 16 corresponding to the second oil injection hole 15. The first oil injection hole 13 and the second oil injection hole 15 are respectively located on both sides of the housing 1 in the axial direction. The cover plate 11 covers the inner side of the second oil injection hole 15 and is provided with a fourth connecting hole 61. The outer ring portion 311 is provided with a side hole 316 connecting the second connecting hole 313. The fourth connecting hole 61 and the side hole 316 are respectively connected to two mounting positions 4.
[0027] The housing 1 is provided with a third oil injection hole 17 and a third oil injection rod 18 corresponding to the third oil injection hole 314 at the middle part, and a test bearing 5 is provided between the housing and the drive shaft 21 at the third oil injection hole 17.
[0028] There are two test bearings 5, and an oil guide ring 6 is provided between the two test bearings 5. The oil guide ring 6 covers the bottom of the third oil injection hole 16, and the oil guide ring 6 is provided with a fourth connecting hole 61. The fourth connecting hole 61 connects the third oil injection hole 17 and the two sides of the guide ring 6 in the axial direction.
[0029] The loading component 3 includes a radial loading rod 32, which is connected to the middle of the housing 1.
[0030] The housing 1 has temperature measuring holes 19 at two mounting positions 4 for inserting thermometers.
[0031] The housing 1 is provided with detection holes 10 on both sides of the third oil injection hole 17 in the axial direction.
[0032] The above examples are merely one preferred embodiment of this utility model. Ordinary variations and substitutions made by those skilled in the art within the scope of this utility model's technical solution are all included within the protection scope of this utility model.
Claims
1. A test fixture for aircraft bearings, comprising a housing, a drive assembly, and a loading assembly, characterized in that: The housing includes a cover plate, an axially penetrating groove, a first oil injection hole, and a first oil injection rod corresponding to the position of the first oil injection hole. The drive assembly includes a drive shaft, which passes through the groove and forms two mounting positions between itself and the housing for mounting the bearing to be tested. The drive shaft includes a hollow inner cavity and several radially extending first connecting holes, which connect the inner cavity and the inner side of the housing. The loading assembly includes an axial loading member, which includes an outer ring and a shaft. The outer ring and the cover plate are respectively located on both sides of the housing along the axial direction, and the outer ring and the cover plate can respectively abut against the outer ring of the bearing to be tested at the adjacent mounting positions. The outer ring covers the inner side of the first oil injection hole and has a second connecting hole. The shaft passes through the inner cavity and has a third connecting hole and an oil groove. The second connecting hole connects to the oil groove, and the third connecting hole connects the oil groove and the inner cavity.
2. The aerospace bearing testing fixture according to claim 1, characterized in that: The housing is provided with a second oil injection hole and a second oil injection rod corresponding to the second oil injection hole. The first oil injection hole and the second oil injection hole are respectively located on both sides of the housing in the axial direction. The cover plate covers the inner side of the second oil injection hole and is provided with a fourth connecting hole. The outer ring is provided with a side hole that connects to the second connecting hole. The fourth connecting hole and the side hole are respectively connected to two mounting positions.
3. The aerospace bearing testing fixture according to claim 2, characterized in that: A third oil injection hole and a corresponding third oil injection rod are provided in the middle of the housing. A test bearing is provided between the housing and the drive shaft at the location corresponding to the third oil injection hole.
4. The aerospace bearing testing fixture according to claim 3, characterized in that: The test bearing consists of two bearings, with an oil guide ring positioned between them. The oil guide ring covers the area below the third oil injection hole and has a fourth connecting hole that connects the third oil injection hole and both sides of the guide ring along the axial direction.
5. The aerospace bearing testing fixture according to claim 1, 2, 3, or 4, characterized in that: The loading assembly includes a radial loading rod connected to the middle of the housing.
6. The aerospace bearing testing fixture according to claim 1, 2, 3, or 4, characterized in that: The housing has temperature measuring holes at two corresponding mounting positions for inserting thermometers.
7. The aerospace bearing testing fixture according to claim 3 or 4, characterized in that: The housing is provided with detection holes on both sides of the third oil injection hole along its axial direction.