A test device and test method for an aero bearing

Abstract

The application provides a test device and test method for an aero bearing, relates to the field of bearing test, and adopts the scheme that the test device comprises a test bushing and a main shaft, a driving motor is connected to the driving end of the main shaft, a test bearing is arranged between the loading end of the main shaft and the test bushing, a fixing base and a moving base are coaxially arranged on the main shaft, the fixing base is detachably connected to one end of the test bushing, the moving base can move along the main shaft, an elastic element is arranged between the fixing base and the moving base, the moving base is located between the fixing base and the test bearing, the end of the moving base can abut against the inner end of the test bearing, a non-contact temperature field acquisition tool is arranged at the end, away from the main shaft, of the test bushing, and the non-contact temperature field acquisition tool can be opposite to the test bearing. The application can conveniently acquire the temperature field change information of the aero bearing.

Description

Technical Field

[0001] This invention relates to the field of bearing testing, and more particularly to a testing apparatus and method for aircraft bearings. Background Technology

[0002] Bearing testing equipment can provide a standardized and reproducible simulated service environment for bearings, accurately simulating key parameters such as load, speed, temperature, and lubrication conditions that bearings experience under actual working conditions. By quantitatively detecting and analyzing core performance indicators such as bearing rotational accuracy, vibration noise, temperature rise characteristics, and fatigue life, the equipment can verify the bearing's design rationality, manufacturing process reliability, and material compatibility.

[0003] In the prior art, Chinese invention patent application CN 114076677 A provides a shaft system structure for a bearing tester, including an axial loading mechanism, a test bushing, and a loading bushing. The area from the loading bushing to the process load body in this device is a standardized process part, while the test end is a replaceable test part. The replaceable test part is designed and processed separately according to different test bearings, which greatly reduces the workload of tooling design. Since the right end of the shaft system is the test bearing part, only this part needs to be disassembled during installation and disassembly, which also greatly reduces the workload of on-site operators. In use, temperature sensors and other sensors are often installed on the test bushing to collect test data of the test bearing.

[0004] For aerospace bearings, interference fits are often used in core components such as engine main shafts and landing gear shafts. However, uneven temperature distribution can lead to differential thermal expansion of the bearing's inner and outer rings, rolling elements, cage, and other components, resulting in uneven clearances. This can cause problems such as uneven load distribution and increased vibration, affecting operational safety. Therefore, it is necessary to monitor temperature field changes during bearing testing. However, when using the above technical solutions, temperature sensors can only be installed on the test bushing to collect temperature data. But temperature sensors can only obtain temperature changes at a single point on the outer ring of the bearing and cannot collect information on the overall temperature field changes of the bearing, which is not conducive to data analysis and cannot meet the testing requirements. Summary of the Invention

[0005] To address the technical problem that existing bearing testing devices cannot meet the requirements for collecting temperature field information of aerospace bearings, this invention provides a testing device and method for aerospace bearings, which can conveniently collect bearing temperature field change information.

[0006] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows: a testing device for aerospace bearings, comprising a test bushing and a main shaft, wherein a drive motor is connected to the drive end of the main shaft, and a test bearing is disposed between the loading end of the main shaft and the test bushing; the device also includes a fixed seat and a movable seat, wherein the fixed seat and the movable seat are coaxially disposed on the main shaft, the fixed seat is detachably connected to one end of the test bushing, the movable seat is movable along the main shaft, an elastic element is disposed between the fixed seat and the movable seat, the movable seat is located between the fixed seat and the test bearing, and the end of the movable seat is capable of abutting against the inner end of the test bearing; a non-contact temperature field acquisition tool is disposed at the end of the test bushing away from the main shaft, and the non-contact temperature field acquisition tool is capable of being opposite the test bearing.

[0007] This invention, by setting a fixed seat and a movable seat, can load the test bearing inside the test device to simulate the working process, without occupying the external space of the device. It also facilitates the placement of a non-contact temperature field acquisition tool on one side of the test bushing, which greatly facilitates the acquisition of temperature field information compared with the prior art.

[0008] Furthermore, the test bushing is equipped with an oil injection rod, the inner hole of the test bushing is a stepped hole, the inner wall of the inner hole is equipped with a mounting platform, the inner surface of the mounting platform is equipped with an oil flow groove, the inside of the mounting platform is also equipped with a flow channel, the flow channel penetrates the mounting platform, the oil flow groove is connected to the flow channel, the inner hole is also equipped with an oil receiving groove, a first plug is detachably installed on the oil receiving groove, and a second plug is detachably installed at the end of the oil flow groove away from the oil receiving groove. When the first plug is removed, the oil in the test bushing can flow out through the oil flow groove, the flow channel and the oil receiving groove. When the second plug is removed, the oil in the test bushing can flow out through the oil flow groove and the flow channel.

[0009] This invention achieves control over the oil circuit in the test bushing by setting up an oil receiving tank and flow channel, and controlling their opening and closing, thereby enabling flexible analysis of metal powder in the oil and meeting various test requirements.

[0010] Furthermore, the fixed base includes a fixed disk, which is sleeved on the main shaft. A boss is provided on the end face of the fixed disk near the movable base, and the elastic element is provided on the end face of the boss. Two spiral grooves with opposite directions of rotation are provided on the hole walls of the fixed disk and the boss. The fixed disk and the main shaft form a non-contact seal through the two spiral grooves with opposite directions of rotation. The fixed disk is detachably connected to the test bushing. The fixed base and the test bushing are also provided with a communicating air inlet.

[0011] This invention forms a non-contact seal through two spiral grooves with opposite directions and an air inlet, avoiding spindle wear caused by contact seals. The wear powder from the spindle could be mixed into the oil, causing errors in the wear analysis of the test bearing.

[0012] Furthermore, a groove is provided on the end face of the movable seat away from the fixed seat, and the movable seat can abut against the inner end of the outer ring of the test bearing.

[0013] The present invention provides grooves to facilitate the outflow of oil from the movable seat and the fixed seat, and also to help the operator overcome the adsorption force between the movable seat and the test bearing, making it easier to remove.

[0014] Furthermore, an eddy current displacement sensor and a vibration sensor are installed on the test bushing, and a bracket is detachably installed on the end face of the mounting platform, on which an optical fiber sensor is installed.

[0015] This invention, through the use of fiber optic sensors, eddy current displacement sensors, and vibration sensors, can meet the needs of various information acquisition in bearing tests, thus expanding the applicability of this device.

[0016] Furthermore, a loading cover plate is detachably provided at the end of the test bushing. The loading cover plate can abut against the outer end of the test bearing. A sealing ring is provided between the loading cover plate and the test bushing. A pressure bearing seat is provided at the outer end of the loading cover plate. The pressure bearing seat can abut against the loading cylinder.

[0017] This invention, by detaching and installing a loading cover plate at the end of the test bushing, meets the testing requirements of using a loading cylinder for loading, enabling stepless and wide-range adjustment of the loading pressure, and further expanding the application range of this device.

[0018] Furthermore, the loading end of the main shaft is provided with a shoulder, and a limiting ring is provided on the main shaft. The limiting ring is located between the shoulder and the test bearing. The two ends of the limiting ring abut against the shoulder and the inner end of the inner ring of the test bearing, respectively. A limiting nut is also provided on the main shaft, which can abut against the outer end of the inner ring of the test bearing.

[0019] Furthermore, a support bushing is provided at the drive end of the spindle, and a support bearing is provided between the support bushing and the drive end of the spindle.

[0020] Furthermore, a radial loading bushing is provided on the main shaft, a radial bearing is provided between the radial loading bushing and the main shaft, and a limit spacer is provided between the radial bearing and the support bearing.

[0021] This invention enables radial loading tests on test bearings using a radial loading bushing.

[0022] Secondly, the present invention also provides a test method for aircraft bearings, using the aforementioned test apparatus for aircraft bearings, comprising the following steps:

[0023] S01: Install the test bearing and test bushing;

[0024] S02: When temperature field information acquisition is required, install the movable seat on the spindle, and install the fixed seat and elastic element in sequence, so that the movable seat abuts against the inner end of the outer ring of the test bearing. Set the non-contact temperature field acquisition tool on one side of the test bushing opposite the test bearing. When temperature field information acquisition is not required, install the fixed seat, and install the loading cover plate and pressure seat at the end of the test bushing, so that the loading cover plate abuts against the outer end of the outer ring of the test bearing, and set the hydraulic cylinder on one side of the pressure seat.

[0025] S03: When it is necessary to analyze the wear of the test bearing by the metal powder in the oil, remove plug one and install plug two. If not, install plug one and remove plug two so that the oil in the test bushing can be recovered by the oil pump.

[0026] S04: Turn on the drive motor and collect information.

[0027] This invention can collect temperature field information and perform wear analysis using metal powder in oil as needed, meeting various experimental requirements and making it more flexible in use.

[0028] As can be seen from the above technical solutions, the present invention has the following advantages:

[0029] This invention provides a testing device and method for aerospace bearings. By setting a fixed base and a movable base, the bearing can be loaded inside the testing device to simulate the working process without occupying external space. This facilitates the placement of a non-contact temperature field acquisition tool on one side of the test bushing, greatly simplifying temperature field information acquisition compared to existing technologies. By setting up an oil receiving groove and flow channel, and controlling their opening and closing, the oil path in the test bushing can be controlled, enabling flexible analysis of metal powder in the oil and meeting various testing requirements. A non-contact seal is formed by two spiral grooves with opposite rotation directions and an air inlet, avoiding the spindle wear caused by contact seals and preventing spindle wear powder from being mixed into the oil. Error analysis of wear in paired bearing tests; the groove design facilitates oil flow from both the moving and fixed seats, and also helps the operator overcome the adhesion between the moving seat and the bearing, making removal easier; the use of fiber optic sensors, eddy current displacement sensors, and vibration sensors meets the diverse information acquisition needs in bearing testing, expanding the applicability of this device; the ability to install and remove a loading cover plate at the end of the test bushing allows for loading with a loading cylinder, enabling stepless and wide-range adjustment of the loading pressure, further enhancing the device's versatility; it can also acquire temperature field information and perform wear analysis using metal powder in the oil, meeting various testing needs and offering greater flexibility. Attached Figure Description

[0030] To more clearly illustrate the technical solution of the present invention, the accompanying drawings used in the description will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a schematic diagram of the structure using an elastic element for internal loading, as shown in Embodiment 1 of the present invention. Figure 1 .

[0032] Figure 2 This is a schematic diagram of the structure using an elastic element for internal loading, as shown in Embodiment 1 of the present invention. Figure 2 .

[0033] Figure 3 This is a schematic diagram of the structure of an embodiment of the present invention using an external loading cylinder. Figure 1 .

[0034] Figure 4 This is a schematic diagram of the structure of an embodiment of the present invention using an external loading cylinder. Figure 2 .

[0035] Figure 5 This is a schematic diagram of the structure of the test bushing in Embodiment 1 of the present invention.

[0036] Figure 6 This is a schematic diagram of the assembly structure of the fixed seat, the movable seat, and the elastic element in Embodiment 1 of the present invention.

[0037] Figure 7 This is a schematic diagram of the loading cover plate in Embodiment 1 of the present invention.

[0038] Figure 8 This is a schematic diagram of the structure of the movable seat in Embodiment 1 of the present invention.

[0039] Figure 9 This is a schematic diagram of the structure of the fixing seat in Embodiment 1 of the present invention.

[0040] In the diagram, 1. Test bushing; 2. Moving seat; 3. Elastic element; 4. Fixed seat; 401. Fixed plate; 402. Boss; 404. Spiral groove; 5. Radial loading bushing; 6. Radial bearing; 7. Support bushing; 8. Support bearing; 9. Main shaft; 901. Drive end; 902. Loading end; 10. Air inlet; 11. Temperature sensor; 12. Oil inlet; 13. Vibration sensor; 14. Plug one; 15. Oil receiving groove; 16. Flow channel; 17. 18. Oil flow groove; 19. Plug 2; 20. Mounting platform; 21. Transparent cover plate; 22. Eddy current displacement sensor; 23. Fiber optic sensor; 24. Bracket; 25. Test bearing; 26. Limit nut; 27. Limit ring; 28. Shoulder 1; 29. ​​Loading cover plate; 20. Clearance hole; 20. Pressure seat; 31. Non-contact temperature field acquisition tool; 32. Loading cylinder; 33. Groove; 34. Limiting spacer ring; 35. Oil injection rod; 36. Inner hole. Detailed Implementation

[0041] To make the objectives, features, and advantages of this invention more apparent and understandable, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0042] Example 1

[0043] like Figures 1 to 4As shown, this embodiment provides a testing device for aircraft bearings, including a test bushing 1 and a main shaft 9. The drive end 901 of the main shaft 9 is connected to a drive motor. The loading end 902 of the main shaft 9 is used to set a test bearing 24 between the test bushing 1 and the main shaft 9. The device also includes a fixed seat 4 and a movable seat 2. The fixed seat 4 and the movable seat 2 are coaxially arranged on the main shaft 9. The fixed seat 4 is detachably connected to one end of the test bushing 1. The movable seat 2 can move along the main shaft 9. An elastic element 3 is provided between the fixed seat 4 and the movable seat 2. The movable seat 2 is located between the fixed seat 4 and the test bearing 24. The end of the movable seat 2 can abut against the inner end of the test bearing 24. A non-contact temperature field acquisition tool 30 is provided at the end of the test bushing 1 away from the main shaft 9. The non-contact temperature field acquisition tool 30 can be opposite to the test bearing 24. The non-contact temperature field acquisition tool 30 can be an infrared thermal imager or an infrared thermal scanner. In this embodiment, an infrared thermal imager is used, and the elastic element 3 is a spring.

[0044] This embodiment, by setting a fixed seat 4 and a movable seat 2, allows the test bearing 24 to be loaded inside the test device to simulate the working process without occupying external space of the device or obstructing the test bearing 24. It also facilitates the placement of a non-contact temperature field acquisition tool 30 on one side of the test bushing 1. Compared with the prior art, this greatly facilitates the acquisition of temperature field information and meets the test requirements for acquiring temperature field information of aerospace bearings under large loading pressure. At the same time, compared with the prior art method of deploying multiple temperature sensors 11 for multi-point temperature information acquisition, the infrared thermal imager can directly generate a continuous thermal image of the bearing surface, presenting the entire temperature field in a visual form. It can not only accurately capture the temperature value at each location, but also clearly display the temperature gradient, hot spot location and diffusion trend, completely restore the thermal distribution state of the bearing, and provide panoramic data support for fault diagnosis.

[0045] When testing aircraft bearings, it is necessary to study their wear; therefore, such as Figures 1 to 5As shown, in this embodiment, the test bushing 1 is provided with an inclined oil inlet hole 12, and an oil spray rod 34 is provided inside the oil inlet hole 12. By controlling the opening and closing of the oil spray rod 34 and the flow rate, the lubrication of the test bearing 24 and the leakage of lubricating oil are controlled. The oil spray rod 34 is inclined, and its installation angle and oil spray volume should be designed to avoid oil splashing from the test bearing 24 during the test, which would contaminate the transparent cover plate 20 and affect the infrared imager's acquisition of the temperature field of the test bearing. The inner hole 35 of the test bushing 1 is a stepped hole, and the test bearing 24 is located at the small end of the inner hole 35. A mounting platform 19 is provided on the hole wall of the inner hole 35, and an oil flow groove 17 is provided on the inner surface of the mounting platform 19. The oil flowing through the test bearing 24 can enter the oil flow groove 17. In this embodiment, the oil flow groove 17 is an arc-shaped groove, which increases the throttling area for oil return and increases the flow velocity. The mounting platform 19 is also provided with a flow channel 16, which is arranged axially and penetrates the mounting platform 19. The oil flow groove 17 is connected to the flow channel 16. An oil receiving groove 15 is also provided on the wall of the larger inner diameter of the inner hole 35. A plug 14 is detachably installed on the oil receiving groove 15. A plug 2 18 is detachably installed at the end of the oil flow groove 17 away from the oil receiving groove 15. When it is necessary to collect oil for wear analysis, the plug 14 is removed, and the oil in the test bushing 1 can flow out through the oil flow groove 17, the flow channel 16 and the oil receiving groove 15. When it is not necessary to perform wear analysis, the plug 2 18 is removed, and the oil in the test bushing 1 can flow out through the oil flow groove 17 and the flow channel 16 and be recovered by the oil pump. In this embodiment, both the plug 14 and the plug 2 18 are connected to the test bushing 1 by threads.

[0046] In this embodiment, when wear analysis is required, it is necessary to ensure that all oil flowing through the test bearing 24 is recovered and analyzed via the oil receiving tank 15. Therefore, a seal needs to be installed between the fixed seat 4 and the main shaft 9. However, since the fixed seat 4 does not rotate with the main shaft 9, if a sealing ring is used for sealing, it will cause wear on the main shaft 9. The metal powder from the wear of the main shaft 9 will mix into the recovered oil, causing analytical errors. Therefore, if... Figure 6 , Figure 8 and Figure 9As shown, in this embodiment, the fixed seat 4 and the spindle 9 employ a non-contact seal. Specifically, the fixed seat 4 includes a fixed disk 401, which is sleeved on the spindle 9. A boss 402 is provided on the end face of the fixed disk 401 near the movable seat 2, and the elastic element 3 is provided on the end face of the boss 402. Two spiral grooves 404 with opposite directions of rotation are provided on the hole walls of the fixed disk 401 and the boss 402. The fixed disk 401 and the spindle 9 form a non-contact seal through the two spiral grooves 404 with opposite directions of rotation. The fixed plate 401 and the test bushing 1 are detachably connected by screws. The fixed base 4 and the test bushing 1 are also provided with a communicating air inlet 10. In this embodiment, the boss 402 is provided with an air inlet 10, which extends inward to between two spiral grooves 404. The fixed plate 401 includes a plate body and a connecting platform at the other end. The spiral groove on the inner wall of the connecting platform has the opposite spiral direction to the spiral groove on the boss 402. The air inlet 10 penetrates the plate body and is located between the two spiral grooves. The two spiral grooves 404 are provided to reduce the pressure on the left side of the test shaft. To prevent oil leakage from the bearing, and on the other hand, to prevent oil from other components from entering the fixed seat 4 from the right side and then into the test bushing 1; with this configuration, through the air inlet 10 and the two spiral grooves 404 with opposite rotation directions, the opposing pumping effect generated by the two spiral grooves 404 when the main shaft 9 rotates creates a high-pressure air film in the area on both sides of the air inlet 10. This air film effectively blocks oil leakage, and the introduction of the air inlet 10 further enhances the pressure stability of the sealing area, thereby achieving a reliable, low-wear non-contact seal without physical contact; furthermore, The movable seat 2 has a groove 32 on its end face away from the fixed seat 4. The movable seat 2 can abut against the inner end of the outer ring of the test bearing 24. By setting the groove 32, on the one hand, when oil enters the movable seat, the oil can flow back to the test bushing 1 under the action of the groove, reducing wear analysis error. On the other hand, the groove 32 makes it easy for the operator to use tools to apply force to overcome the adsorption force between the movable seat 2 and the test bearing 24, making it easy to remove. In this embodiment, there are two flow channels 16, which are respectively opposite to the groove 32 of the movable seat 2 and the position of the elastic element 3.

[0047] To improve the versatility of this device and meet the needs of applying large axial loads when temperature field acquisition is not required, such as Figure 3 , Figure 4 and Figure 7As shown, in this embodiment, the device can also be loaded by a hydraulic cylinder. Specifically, a loading cover plate 28 is detachably installed at the end of the test bushing 1 by screws. The inner side of the loading cover plate 28 can extend into the interior of the test bushing 1 and abut against the outer end of the test bearing 24. A sealing ring is provided between the loading cover plate 28 and the test bushing 1. The outer end of the loading cover plate 28 is connected to a pressure bearing seat 29 by bolts. The pressure bearing seat 29 can abut against the loading hydraulic cylinder 31. The loading hydraulic cylinder 31 can provide a large and continuously changing pressure to meet the test requirements. At this time, it is generally not necessary to collect the temperature field information of the test bearing 24. When a large axial load is applied without the requirement for temperature field collection, the device does not need to be installed with a moving seat 2 and an elastic element 3.

[0048] Aerospace bearing testing requires information collection from various aspects according to testing requirements. To meet these requirements, in this embodiment, for example... Figures 1 to 4 As shown, an eddy current displacement sensor 21 and a vibration sensor 13 are installed on the test bushing 1. A bracket 23 is detachably mounted on the end face of the mounting platform 19 via screws, and an optical fiber sensor 22 is mounted on the bracket 23. In this embodiment, three eddy current displacement sensors 21 are installed in corresponding mounting holes in the test bushing 1, arranged radially along the test bushing 1, with the signal acquisition end close to the end of the spindle 9, capable of acquiring the axis trajectory of the spindle 9 and monitoring the working state of the test bearing 24. The vibration sensor 13 is set on the circumferential surface of the test bushing 1 to acquire the vibration signal of the test bearing 24, combined with the metal powder in the oil. The relationship between wear and vibration signals is analyzed; the acquisition end of the fiber optic sensor is opposite to the cage of the test bearing 24. The fiber optic sensor 22 is used to measure the rotational speed of the cage of the test bearing 24. By measuring the rotational speed of the cage, it is possible to analyze whether the test bearing 24 slips under the current working conditions; when the hydraulic cylinder is used for loading, it is necessary to pay attention to the temperature information of key points. In order to meet the requirements of key point temperature information acquisition, mounting holes are provided on the circumferential surface of the test bushing 1. Temperature sensors 11 are installed in the mounting holes. In this embodiment, six are set and evenly distributed along the circumferential surface of the test bushing 1. The acquisition end of the temperature sensor 11 is in contact with the outer ring of the bearing.

[0049] In this embodiment, as Figure 3As shown, the loading end 902 of the spindle 9 is provided with a shoulder 27. A limiting ring 26 is provided on the spindle 9, which is located between the shoulder 27 and the test bearing 24. The two ends of the limiting ring 26 abut against the inner end of the inner ring of the shoulder 27 and the test bearing 24, respectively. A limiting nut 25 is also detachably provided on the spindle 9, which can abut against the outer end of the inner ring of the test bearing 24. This arrangement facilitates the installation of the test bearing. 24; When installing the test bearing 24, install the limiting ring 26 on the main shaft 9 and abut it against the shaft shoulder 27, then install the test bearing 24 so that the limiting ring 26 abuts against the inner end of the inner ring of the test bearing 24, and then tighten the limiting nut 25 so that the limiting nut 25 abuts against the outer end of the inner ring of the test bearing 24; after installing the test bearing 24, the test bushing 1 can be installed. The test bushing 1 is interference-fitted with the outer ring of the bearing so that the outer end face of the bearing is flush with the end face of the mounting platform 19 of the test bushing 1.

[0050] like Figure 1 As shown, in order to support the spindle 9 and reduce the impact of spindle 9 error on the test bearing 24, a support bushing 7 is provided at the drive end 901 of the spindle 9, and a support bearing 8 is provided between the support bushing 7 and the drive end 901 of the spindle 9. The spindle 9 is connected to the motor shaft of the drive motor through a coupling.

[0051] To meet the testing requirements for radial loading of the test bearing 24, such as Figure 1 As shown, in this embodiment, a radial loading bushing 5 is also provided on the main shaft 9, a radial bearing 6 is provided between the radial loading bushing 5 and the main shaft 9, and a limiting spacer 33 is provided between the radial bearing 6 and the support bearing 8, with the limiting spacer 33 having an interference fit with the main shaft 9.

[0052] like Figure 1 and Figure 7 As shown, in this embodiment, the end of the test bushing 1 is also provided with a transparent cover plate 20 by bolt removal to prevent internal oil leakage and at the same time to prevent the infrared thermometer from collecting temperature field information; the loading end 902 is provided with a clearance hole 281 at the corresponding position to facilitate the passage of the temperature sensor 11 and the eddy current displacement sensor 21.

[0053] In this embodiment, the parameters of the elastic element 3 are as follows: elastic coefficient 9.78 N / mm, material SWP, outer diameter 6 mm, length 30 mm, maximum load 73.5 N, wire diameter 1.1 mm, and quantity 20.

[0054] Example 2

[0055] This embodiment also provides a test method for aircraft bearings, using the test apparatus for aircraft bearings from Embodiment 1, including the following steps:

[0056] S01: Install test bearing 24 and test bushing 1;

[0057] S02: When temperature field information acquisition is required, the movable seat 2 is installed on the main shaft 9, and the fixed seat 4 and elastic element 3 are installed in sequence, so that the movable seat 2 abuts against the inner end of the outer ring of the test bearing 24. The non-contact temperature field acquisition tool 30 is set on one side of the test bushing 1 opposite to the test bearing 24. When temperature field information acquisition is not required and a large axial load is required, the fixed seat 4 is installed, the elastic element 3 is not required, and the loading cover plate 28 and the pressure seat 29 are installed at the end of the test bushing 1, so that the loading cover plate 28 abuts against the outer end of the outer ring of the test bearing 24. A hydraulic cylinder is set on one side of the pressure seat.

[0058] S03: When it is necessary to analyze the wear of the test bearing 24 by the metal powder in the oil, remove plug 14 and install plug 2 18. If not, install plug 14 and remove plug 2 18 so that the oil in the test bushing 1 can be recovered by the oil pump.

[0059] S04: Turn on the drive motor and collect information.

[0060] In S04, according to the test requirements, the corresponding sensors are installed. When it is necessary to collect the shaft center trajectory, three eddy current displacement sensors 21 are installed into the corresponding mounting holes of the test bushing 1. When it is necessary to collect vibration signals, the vibration sensor 13 is installed on the mounting surface of the outer circumference of the test bushing 1 by bolts. When it is necessary to detect whether the bearing is slipping, the bracket 23 is installed on the end face of the mounting platform 19, and then the fiber optic sensor 22 is installed. When it is necessary to collect the temperature of the set point, the temperature sensor 11 is installed on the corresponding mounting hole of the test bushing 1. When it is necessary to apply radial load, a radial load is applied to the radial loading bushing 5.

[0061] As can be seen from the above specific embodiments, the present invention has the following beneficial effects:

[0062] 1. By setting a fixed seat 4 and a movable seat 2, the test bearing 24 can be loaded inside the test device to simulate the working process, without occupying the external space of the device. This facilitates the arrangement of a non-contact temperature field acquisition tool 30 on one side of the test bushing 1, which greatly facilitates the acquisition of temperature field information compared with the existing technology.

[0063] 2. By setting up the oil receiving tank 15 and the flow channel 16, and controlling their opening and closing, the oil circuit in the test bushing 1 can be controlled, thereby achieving flexibility in the analysis of metal powder in the oil and meeting various test requirements.

[0064] 3. A non-contact seal is formed by two spiral grooves 404 with opposite directions and an air inlet 10, avoiding wear of the main shaft 9 caused by contact sealing. The powder from the wear of the main shaft 9 is mixed into the oil, causing errors in the wear analysis of the test bearing 24.

[0065] 4. By setting the groove 32, on the one hand, it is convenient for the oil in the movable seat 2 and the fixed seat 4 to flow out; on the other hand, the groove 32 makes it easier for the operator to overcome the adsorption force between the movable seat 2 and the test bearing 24, making it easy to remove.

[0066] 5. The fiber optic sensor, eddy current displacement sensor 21 and vibration sensor 13 can meet the needs of collecting various information in bearing tests, thus expanding the applicability of this device.

[0067] 6. By removing and installing the loading cover plate 28 at the end of the test bushing 1 to meet the loading requirements of the loading cylinder 31, the test needs of stepless adjustment and wide range adjustment of the loading pressure are realized, further improving the application range of this device;

[0068] 7. It can collect temperature field information and perform wear analysis using metal powder in oil as needed, meeting various test requirements and making it more flexible to use.

[0069] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A testing apparatus for aircraft bearings, comprising a test bushing (1) and a spindle (9), wherein a drive motor is connected to a drive end (901) of the spindle (9), and a test bearing is disposed between the loading end (902) of the spindle (9) and the test bushing (1), characterized in that, It also includes a fixed seat (4) and a movable seat (2), the fixed seat (4) and the movable seat (2) being coaxially mounted on the main shaft (9). The fixed seat (4) is detachably connected to one end of the test bushing (1), and the movable seat (2) is movable along the main shaft (9). An elastic element (3) is provided between the fixed seat (4) and the movable seat (2). The movable seat (2) is located between the fixed seat (4) and the test bearing, and the end of the movable seat (2) can abut against the inner end of the test bearing. A non-contact temperature field acquisition tool (30) is provided at one end of the test bushing (1) away from the main shaft (9). The non-contact temperature field acquisition tool (30) can be opposite to the test bearing. When temperature field information needs to be acquired, the movable seat (2) is installed on the main shaft (9), and the fixed seat (4) and elastic element (3) are installed in sequence, so that the movable seat (2) abuts against the inner end of the outer ring of the test bearing, and the non-contact temperature field acquisition tool (30) is set on one side of the test bushing (1) opposite to the test bearing. The end of the test bushing (1) is also detachably provided with a loading cover plate (28). The loading cover plate (28) can abut against the outer end of the test bearing. A sealing ring is provided between the loading cover plate (28) and the test bushing (1). A pressure seat (29) is provided at the outer end of the loading cover plate (28). The pressure seat (29) can abut against the loading cylinder (31). When temperature field information collection is not required, a fixing seat (4) is installed, and the loading cover plate (28) and pressure seat (29) are installed at the end of the test bushing (1) so that the loading cover plate (28) abuts against the outer end of the outer ring of the test bearing. A hydraulic cylinder is provided on one side of the pressure seat (29). The test bushing (1) is provided with an oil injection rod (34). The inner hole (35) of the test bushing (1) is a stepped hole. An installation platform (19) is provided on the hole wall of the inner hole (35). An oil flow groove (17) is provided on the inner surface of the installation platform (19). A flow channel (16) is also provided inside the installation platform (19). The flow channel (16) penetrates the installation platform (19). The oil flow groove (17) is connected to the flow channel (16). An oil receiving groove (15) is also provided on the inner hole (35). A plug (14) is disassembled and installed on the oil receiving groove (15). The end of the oil flow groove (17) away from the oil receiving groove (15) is disassembled. The test bushing (1) is equipped with a second plug (18). When the first plug (14) is removed, the oil in the test bushing (1) can flow out through the oil flow groove (17), the flow channel (16) and the oil receiving groove (15). When the second plug (18) is removed, the oil in the test bushing (1) can flow out through the oil flow groove (17) and the flow channel (16). When it is necessary to analyze the wear of the test bearing by the metal powder in the oil, the first plug (14) is removed and the second plug (18) is installed. If it is not necessary, the first plug (14) is installed and the second plug (18) is removed, so that the oil in the test bushing (1) can be recovered by the oil pump.

2. The testing apparatus for aircraft bearings as described in claim 1, characterized in that, The fixed base (4) includes a fixed plate (401), which is sleeved on the main shaft (9). A boss (402) is provided on the end face of the fixed plate (401) near the moving base (2). The elastic element (3) is provided on the end face of the boss (402). Two spiral grooves (404) with opposite directions are provided on the hole walls of the fixed plate (401) and the boss (402). The fixed plate (401) and the main shaft (9) form a non-contact seal through the two spiral grooves (404) with opposite directions. The fixed plate (401) is detachably connected to the test bushing (1). The fixed base (4) and the test bushing (1) are also provided with a communicating air inlet (10).

3. The testing apparatus for aircraft bearings as described in claim 2, characterized in that, The movable seat (2) has a groove (32) on its end face away from the fixed seat (4), and the movable seat (2) can abut against the inner end of the outer ring of the test bearing.

4. The testing apparatus for aircraft bearings as described in claim 1, characterized in that, A temperature sensor (11), an eddy current displacement sensor (21), and a vibration sensor (13) are installed on the test bushing (1). A bracket (23) is detachably installed on the end face of the mounting platform (19), and an optical fiber sensor is installed on the bracket (23).

5. The testing apparatus for aircraft bearings as described in claim 1, characterized in that, The loading end (902) of the main shaft (9) is provided with a shoulder (27). A limiting ring (26) is provided on the main shaft (9). The limiting ring (26) is located between the shoulder (27) and the test bearing. The two ends of the limiting ring (26) abut against the shoulder (27) and the inner end of the inner ring of the test bearing, respectively. A limiting nut (25) is also provided on the main shaft (9). The limiting nut (25) can abut against the outer end of the inner ring of the test bearing.

6. The testing apparatus for aircraft bearings as described in claim 5, characterized in that, The drive end (901) of the main shaft (9) is provided with a support bushing (7), and a support bearing (8) is provided between the support bushing (7) and the drive end (901) of the main shaft (9).

7. The testing apparatus for aircraft bearings as described in claim 6, characterized in that, A radial loading bushing (5) is also provided on the main shaft (9), and a radial bearing (6) is provided between the radial loading bushing (5) and the main shaft (9), and a limiting spacer (33) is provided between the radial bearing (6) and the support bearing (8).

8. A test method for aircraft bearings, characterized in that, The testing apparatus for aerospace bearings as described in claim 7 includes the following steps: S01: Install the test bearing and test bushing (1); S02: When temperature field information collection is required, the movable seat (2) is installed on the main shaft (9), and the fixed seat (4) and elastic element (3) are installed in sequence, so that the movable seat (2) abuts against the inner end of the outer ring of the test bearing, and the non-contact temperature field acquisition tool (30) is set on one side of the test bushing (1) opposite to the test bearing; when temperature field information collection is not required, the fixed seat (4) is installed, and the loading cover plate (28) and the pressure seat (29) are installed at the end of the test bushing (1), so that the loading cover plate (28) abuts against the outer end of the outer ring of the test bearing, and a hydraulic cylinder is set on one side of the pressure seat (29); S03: When it is necessary to analyze the wear of the test bearing by the metal powder in the oil, remove plug one (14) and install plug two (18). If not, install plug one (14) and remove plug two (18) so that the oil in the test bushing (1) can be recovered by the oil pump. S04: Turn on the drive motor and collect information.

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