CN212158966U - High thrust aircraft engine 4 fulcrum bearing seal dynamic test platform - Google Patents
High thrust aircraft engine 4 fulcrum bearing seal dynamic test platform Download PDFInfo
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- CN212158966U CN212158966U CN202020937820.4U CN202020937820U CN212158966U CN 212158966 U CN212158966 U CN 212158966U CN 202020937820 U CN202020937820 U CN 202020937820U CN 212158966 U CN212158966 U CN 212158966U
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- 238000012360 testing method Methods 0.000 title claims abstract description 111
- 238000007789 sealing Methods 0.000 claims abstract description 92
- 238000000034 method Methods 0.000 abstract description 34
- 238000004088 simulation Methods 0.000 abstract 1
- 239000007788 liquid Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses a 4 fulcrum bearing seal dynamic test platform of high thrust aircraft engine, including operation panel, motor, casing, tighrening ring, bearing, closing plate one, closing plate two and pressure test interface, its characterized in that: the operation table is arranged on the support, the motor is arranged on the vertical plate, the shell is arranged on the stand column, the fastening ring is arranged on the rotating shaft, the bearing is arranged on the rotating shaft, and the first sealing plate is arranged at one end of the shell through the mounting bolt. The utility model discloses all be provided with sealed piece on closing plate one, closing plate two, can fix from the both ends of casing through closing plate one, closing plate two, make casing simulation aircraft engine operating condition, improved the leakproofness between closing plate one and casing and closing plate two and the casing through sealed piece, and then strengthen the leakproofness of engine bearing in the dynamic test process, improve the precision of dynamic test result.
Description
Technical Field
The utility model relates to a testing arrangement specifically relates to a 4 fulcrum bearing seal dynamic test platform of high thrust aircraft engine.
Background
The engine bearing seal plays an important role in the working process of a high-thrust aircraft engine, in order to improve the quality performance of the engine bearing seal product, the engine bearing seal is subjected to dynamic testing after the engine bearing seal is processed, and the conventional engine bearing seal dynamic testing device has the problems of low sealing performance, poor stability of the engine bearing seal in the dynamic testing process and low accuracy of the engine bearing seal dynamic testing result.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a not high, the sealed not high problem of dynamic test result precision of engine bearing of the leakproofness that exists to current engine bearing dynamic testing arrangement, engine bearing seal stability is not good in the dynamic test process, engine bearing seal, provide a structural design is reasonable, sealing performance is good, engine bearing seal stability is high in the dynamic test process, the sealed high 4 fulcrum bearing seal dynamic test platforms of big thrust aircraft engine of dynamic test result precision of engine bearing.
The utility model provides a technical scheme that its technical problem adopted is:
the utility model provides a 4 fulcrum bearing seal dynamic test platforms of big thrust aircraft engine, includes operation panel, motor, casing, tighrening ring, bearing, closing plate one, closing plate two and pressure test interface, its characterized in that: the vertical plate and the upright post are vertically arranged on the operating platform, the operating platform is connected with the vertical plate and the upright post through welding, the connecting strength between the operating platform and the vertical plate and the upright post is enhanced, the structural strength of the dynamic test platform is improved, and further, the stability of the engine bearing seal in the test process is improved, the motor is arranged on the vertical plate, the rotating shaft is arranged on the motor and is arranged in parallel with the operating platform, the motor is arranged on the vertical plate through bolts, the installation efficiency of the motor and the stability after installation are improved, the shell is arranged on the upright post, the shell wraps the rotating shaft, the top part in the shell is provided with a fixed block, the bottom part in the shell is provided with an oil supply interface and an air supply interface, the bottom part in the shell is provided with an oil return interface, and the fixed block and the cushion block in the shell can fix the engine bearing in, the stability of the engine bearing in the dynamic test process is improved, the accuracy of the dynamic test result is enhanced, high-temperature oil with the same temperature when the engine runs can be injected into the shell through the oil supply interface and the oil return interface to simulate the working condition of the aircraft engine, the dynamic test can be carried out on the engine bearing under the actual working condition of the aircraft engine, the accuracy of the test result of the engine bearing is improved, gas can be injected into the shell through the air supply interface to carry out the dynamic test on the sealing performance between the rotating shaft and the engine bearing, the service life of the engine bearing sealing is convenient to calculate, the fastening ring is arranged on the rotating shaft, the bearing is arranged between the fastening ring and the fixed block, and the fixture block on the connecting block is clamped with the fixed block and the cushion block, so that the engine bearing is sealed and firmly fixed between the fastening ring and, the stability of the engine bearing seal in the dynamic test process is improved, the accuracy of the dynamic test result is enhanced, the number of the connecting blocks is set to be 4, the clamping blocks on the connecting blocks are enabled to fix the engine bearing, the stability of the engine bearing in the dynamic test process is enhanced, the accuracy of the dynamic test result of the engine bearing is improved, the first sealing plate is arranged at one end of the shell through the mounting bolts, the second sealing plate is arranged at the other end of the shell through the mounting bolts and can be fixed from two ends of the shell through the first sealing plate and the second sealing plate, the shell is enabled to simulate the working state of an aircraft engine, the sealing performance between the first sealing plate and the shell and between the second sealing plate and the shell is improved through the sealing blocks, the sealing performance of the engine bearing in the dynamic test process is further enhanced, the accuracy of the dynamic test result is improved, and the mounting plate is arranged on the pressure test interface, the mounting plate is arranged at the top of the shell through the mounting bolt, and the pressure in the shell can be detected when the shell is filled with liquid oil or gas through the pressure test interface, so that the tightness of the engine bearing in the working process can be tested conveniently, and the quality performance of the engine bearing is improved.
Preferably, the motor is set as a servo motor, the motor drives the rotating shaft to rotate in the forward direction or the reverse direction, the speed of the rotating shaft is enabled to reach the running speed of the engine, the rotating shaft drives the rotating shaft to rotate in the forward direction or the reverse direction in the bearing, the actual working condition of the running of the aircraft engine is simulated, the online data acquisition is carried out on the actual running performance of the sealing of the engine bearing, the dynamic test is carried out on the sealing of the engine bearing, and the product quality of the sealing of the engine bearing can be improved.
Preferably, the fastening ring on be provided with the connecting block, be provided with the fixture block on the connecting block to pass through construction bolt setting with the fixture block on the fixed block, with fixture block card post fixed block, the cushion on the connecting block, make the engine bearing seal firmly fix between fastening ring and cushion, improve the stability of engine bearing seal in the dynamic testing process, strengthen the precision of dynamic testing result, set up the quantity of connecting block to 4, make the fixture block on the connecting block fix the engine bearing, strengthen the stability of engine bearing in the dynamic testing process, improve the precision of engine bearing dynamic testing result.
Preferably, the first sealing plate and the second sealing plate are provided with sealing blocks, the first sealing plate and the second sealing plate can be fixed from two ends of the shell, the shell can simulate the working state of an aircraft engine, the sealing performance between the first sealing plate and the shell and between the second sealing plate and the shell is improved through the sealing blocks, the sealing performance of an engine bearing in a dynamic test process is further enhanced, and the accuracy of a dynamic test result is improved.
Preferably, the second sealing plate is provided with a connecting ring, the connecting ring is sleeved on the rotating shaft, and the connecting ring is sleeved on the rotating shaft, so that a space can be provided for the rotation of the rotating shaft, the dynamic testing efficiency of the engine bearing is improved, and the labor intensity of workers is reduced.
Has the advantages that: the utility model discloses be provided with the connecting block on the tighrening ring, be provided with the fixture block on the connecting block, and pass through construction bolt with the fixture block and set up on the fixed block, with the fixture block card post fixed block on the connecting block, the cushion, make the engine bearing seal firmly fix between tighrening ring and cushion, improve the stability of engine bearing seal in the dynamic test process, strengthen the precision of dynamic test result, set up the quantity of connecting block into 4, make the fixture block on the connecting block fix the engine bearing, strengthen the stability of engine bearing in the dynamic test process, improve the precision of engine bearing dynamic test result.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic view of a part of the structure of the present invention, illustrating the connection structure of the fastening ring and the connecting block.
Fig. 3 is a schematic view of a part of the structure of the present invention, illustrating a connection structure of the first sealing plate and the sealing block.
Fig. 4 is a schematic view of another embodiment of the present invention.
In the figure: 1. the device comprises an operation table, 2. a motor, 3. a shell, 4. a fastening ring, 5. a bearing, 6. a first sealing plate, 7. a second sealing plate, 8. a pressure test interface, 9. a vertical plate, 10. an upright post, 11. a rotating shaft, 12. a fixed block, 13. a cushion block, 14. an oil supply interface, 15. an air supply interface, 16. an oil return interface, 17. a connecting block, 18. a clamping block, 19. a mounting bolt, 20. a sealing block, 21. a connecting ring, 22. a mounting plate and 23. a sealing ring.
Detailed Description
The present invention will be described in more detail with reference to the accompanying drawings.
The first embodiment is as follows:
as shown in figures 1-3: the utility model provides a 4 fulcrum bearing 5 sealed dynamic test platforms of high thrust aircraft engine, includes operation panel 1, motor 2, casing 3, tighrening ring 4, bearing 5, closing plate 6, closing plate two 7 and pressure test interface 8, its characterized in that: the vertical plate 9 and the upright post 10 are vertically arranged on the operating platform 1, the operating platform 1 is connected with the vertical plate 9 and the upright post 10 through welding, the connecting strength between the operating platform 1 and the vertical plate 9 and the upright post 10 is enhanced, the structural strength of the dynamic test bench is improved, and the stability of the engine bearing seal in the test process is further improved, the motor 2 is arranged on the vertical plate 9, the rotating shaft 11 is arranged on the motor 2, the rotating shaft 11 is arranged in parallel with the operating platform 1, the motor 2 is arranged on the vertical plate 9 through bolts, the mounting efficiency of the motor 2 and the stability after mounting are improved, the shell 3 is arranged on the upright post 10, the rotating shaft 11 is wrapped on the shell 3, the fixed block 12 is arranged at the inner top of the shell 3, the cushion block 13 is arranged at the inner bottom of the shell 3, the oil supply interface 14 and the air supply interface 15 are arranged at the top of the shell 3, and the interface, the fixed block 12 and the cushion block 13 in the shell 3 can fix the engine bearing in the dynamic test process, improve the stability of the engine bearing in the dynamic test process and enhance the accuracy of the dynamic test result, high-temperature oil with equal temperature during the operation of an engine can be injected into the shell 3 through the oil supply interface 14 and the oil return interface 16 to simulate the working condition of an aircraft engine, the dynamic test can be carried out on the actual working condition of the aircraft engine by the engine bearing, the accuracy of the test result of the engine bearing can be improved, gas can be injected into the shell 3 through the air supply interface 15 to dynamically test the sealing property between the rotating shaft 11 and the engine bearing, so that the service life of the engine bearing seal can be conveniently calculated, the fastening ring 4 is arranged on the rotating shaft 11, the bearing 5 is arranged on the rotating shaft 11, and the bearing 5 is arranged between the fastening ring 4 and the fixed block 12, the fixture block 18 on the connecting block 17 is clamped with the column fixing block 12 and the cushion block 13, so that the engine bearing is tightly and tightly fixed between the fastening ring 4 and the cushion block 13, the stability of the engine bearing in the dynamic testing process is improved, the accuracy of the dynamic testing result is enhanced, the number of the connecting block 17 is set to be 4, the fixture block 18 on the connecting block 17 fixes the engine bearing, the stability of the engine bearing in the dynamic testing process is enhanced, and the accuracy of the dynamic testing result of the engine bearing is enhanced, the sealing plate I6 is arranged at one end of the shell 3 through the mounting bolt 19, the sealing plate II 7 is arranged at the other end of the shell 3 through the mounting bolt 19, the shell 3 can be fixed from two ends of the shell 3 through the sealing plate I6 and the sealing plate II 7, so that the shell 3 simulates the working state of an aircraft engine, and the sealing performance between the sealing plate I6 and the shell 3 and between the sealing plate II 7 and the shell, and then strengthen the leakproofness of engine bearing in dynamic test process, improve the precision of dynamic test result, pressure test interface 8 on be provided with mounting panel 22 to set up mounting panel 22 at casing 3 top through mounting bolt 19, can detect the pressure in the casing 3 when casing 3 pours into liquid oil or pours into gas into through pressure test interface 8, be convenient for test the leakproofness of engine bearing in the course of the work, improve the quality performance of engine bearing.
Preferably, the motor 2 is set as a servo motor, the motor 2 drives the rotating shaft 11 to rotate in the forward direction or the reverse direction, so that the speed of the rotating shaft 11 reaches the running speed of the engine, the rotating shaft 11 drives the rotating shaft to rotate in the forward direction or the reverse direction in the bearing 5, the actual working condition of the running of the aircraft engine is simulated, the online data acquisition is carried out on the actual running performance of the sealing of the engine bearing, the dynamic test is carried out on the sealing of the engine bearing, and the product quality of the sealing of the engine bearing can be improved.
Preferably, the fastening ring 4 is provided with the connecting block 17, the connecting block 17 is provided with the fixture block 18, the fixture block 18 is arranged on the fixing block 12 through the mounting bolt 19, the fixture block 18 on the connecting block 17 is clamped with the column fixing block 12 and the cushion block 13, so that the engine bearing is tightly and firmly fixed between the fastening ring 4 and the cushion block 13 in a sealing manner, the stability of the engine bearing in the dynamic testing process is improved, the accuracy of the dynamic testing result is enhanced, the number of the connecting blocks 17 is set to be 4, the fixture block 18 on the connecting block 17 is used for fixing the engine bearing, the stability of the engine bearing in the dynamic testing process is enhanced, and the accuracy of the dynamic testing result of the engine bearing is improved.
Preferably, the first sealing plate 6 and the second sealing plate 7 are both provided with a sealing block 20, the first sealing plate 6 and the second sealing plate 7 can be fixed from two ends of the shell 3, so that the shell 3 simulates the working state of an aircraft engine, the sealing performance between the first sealing plate 6 and the shell 3 and between the second sealing plate 7 and the shell 3 is improved through the sealing blocks 20, the sealing performance of an engine bearing in the dynamic testing process is further enhanced, and the accuracy of a dynamic testing result is improved.
Preferably, the second sealing plate 7 is provided with the connecting ring 21, the connecting ring 21 is sleeved on the rotating shaft 11, and the connecting ring 21 is sleeved on the rotating shaft 11, so that a space can be provided for the rotation of the rotating shaft 11, the dynamic testing efficiency of the engine bearing is improved, and the labor intensity of workers is reduced.
Example two:
as shown in fig. 4: the utility model provides a 4 fulcrum bearing 5 sealed dynamic test platforms of high thrust aircraft engine, includes operation panel 1, motor 2, casing 3, tighrening ring 4, bearing 5, closing plate 6, closing plate two 7 and pressure test interface 8, its characterized in that: the vertical plate 9 and the upright post 10 are vertically arranged on the operating platform 1, the operating platform 1 is connected with the vertical plate 9 and the upright post 10 through welding, the connecting strength between the operating platform 1 and the vertical plate 9 and the upright post 10 is enhanced, the structural strength of the dynamic test bench is improved, and the stability of the engine bearing seal in the test process is further improved, the motor 2 is arranged on the vertical plate 9, the rotating shaft 11 is arranged on the motor 2, the rotating shaft 11 is arranged in parallel with the operating platform 1, the motor 2 is arranged on the vertical plate 9 through bolts, the mounting efficiency of the motor 2 and the stability after mounting are improved, the shell 3 is arranged on the upright post 10, the rotating shaft 11 is wrapped on the shell 3, the fixed block 12 is arranged at the inner top of the shell 3, the cushion block 13 is arranged at the inner bottom of the shell 3, the oil supply interface 14 and the air supply interface 15 are arranged at the top of the shell 3, and the interface, the fixed block 12 and the cushion block 13 in the shell 3 can fix the engine bearing in the dynamic test process, improve the stability of the engine bearing in the dynamic test process and enhance the accuracy of the dynamic test result, high-temperature oil with equal temperature during the operation of an engine can be injected into the shell 3 through the oil supply interface 14 and the oil return interface 16 to simulate the working condition of an aircraft engine, the dynamic test can be carried out on the actual working condition of the aircraft engine by the engine bearing, the accuracy of the test result of the engine bearing can be improved, gas can be injected into the shell 3 through the air supply interface 15 to dynamically test the sealing property between the rotating shaft 11 and the engine bearing, so that the service life of the engine bearing seal can be conveniently calculated, the fastening ring 4 is arranged on the rotating shaft 11, the bearing 5 is arranged on the rotating shaft 11, and the bearing 5 is arranged between the fastening ring 4 and the fixed block 12, the fixture block 18 on the connecting block 17 is clamped with the column fixing block 12 and the cushion block 13, so that the engine bearing is tightly and tightly fixed between the fastening ring 4 and the cushion block 13, the stability of the engine bearing in the dynamic testing process is improved, the accuracy of the dynamic testing result is enhanced, the number of the connecting block 17 is set to be 4, the fixture block 18 on the connecting block 17 fixes the engine bearing, the stability of the engine bearing in the dynamic testing process is enhanced, and the accuracy of the dynamic testing result of the engine bearing is enhanced, the sealing plate I6 is arranged at one end of the shell 3 through the mounting bolt 19, the sealing plate II 7 is arranged at the other end of the shell 3 through the mounting bolt 19, the shell 3 can be fixed from two ends of the shell 3 through the sealing plate I6 and the sealing plate II 7, so that the shell 3 simulates the working state of an aircraft engine, and the sealing performance between the sealing plate I6 and the shell 3 and between the sealing plate II 7 and the shell, and then strengthen the leakproofness of engine bearing in dynamic test process, improve the precision of dynamic test result, pressure test interface 8 on be provided with mounting panel 22 to set up mounting panel 22 at casing 3 top through mounting bolt 19, can detect the pressure in the casing 3 when casing 3 pours into liquid oil or pours into gas into through pressure test interface 8, be convenient for test the leakproofness of engine bearing in the course of the work, improve the quality performance of engine bearing.
Preferably, the motor 2 is set as a servo motor, the motor 2 drives the rotating shaft 11 to rotate in the forward direction or the reverse direction, so that the speed of the rotating shaft 11 reaches the running speed of the engine, the rotating shaft 11 drives the rotating shaft to rotate in the forward direction or the reverse direction in the bearing 5, the actual working condition of the running of the aircraft engine is simulated, the online data acquisition is carried out on the actual running performance of the sealing of the engine bearing, the dynamic test is carried out on the sealing of the engine bearing, and the product quality of the sealing of the engine bearing can be improved.
Preferably, the fastening ring 4 is provided with the connecting block 17, the connecting block 17 is provided with the fixture block 18, the fixture block 18 is arranged on the fixing block 12 through the mounting bolt 19, the fixture block 18 on the connecting block 17 is clamped with the column fixing block 12 and the cushion block 13, so that the engine bearing is tightly and firmly fixed between the fastening ring 4 and the cushion block 13 in a sealing manner, the stability of the engine bearing in the dynamic testing process is improved, the accuracy of the dynamic testing result is enhanced, the number of the connecting blocks 17 is set to be 4, the fixture block 18 on the connecting block 17 is used for fixing the engine bearing, the stability of the engine bearing in the dynamic testing process is enhanced, and the accuracy of the dynamic testing result of the engine bearing is improved.
Preferably, the first sealing plate 6 and the second sealing plate 7 are both provided with a sealing block 20, the first sealing plate 6 and the second sealing plate 7 can be fixed from two ends of the shell 3, so that the shell 3 simulates the working state of an aircraft engine, the sealing performance between the first sealing plate 6 and the shell 3 and between the second sealing plate 7 and the shell 3 is improved through the sealing blocks 20, the sealing performance of an engine bearing in the dynamic testing process is further enhanced, and the accuracy of a dynamic testing result is improved.
Preferably, the second sealing plate 7 is provided with the connecting ring 21, the connecting ring 21 is sleeved on the rotating shaft 11, and the connecting ring 21 is sleeved on the rotating shaft 11, so that a space can be provided for the rotation of the rotating shaft 11, the dynamic testing efficiency of the engine bearing is improved, and the labor intensity of workers is reduced.
Preferably, a sealing ring 23 is arranged between the first sealing plate 6 and the rotating shaft 11, and the sealing performance between the first sealing plate 6 and the rotating shaft 11 is improved through the sealing ring 23, so that the sealing performance of the shell 3 during dynamic testing of the engine bearing is improved, the accuracy of a dynamic testing result of the engine bearing is improved, and the quality performance of the engine bearing is enhanced.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
The utility model discloses the part that does not relate to all is the same with prior art or can adopt prior art to realize.
Claims (5)
1. The utility model provides a 4 fulcrum bearing seal dynamic test platforms of big thrust aircraft engine, includes operation panel, motor, casing, tighrening ring, bearing, closing plate one, closing plate two and pressure test interface, its characterized in that: the operating platform is vertically provided with a vertical plate and an upright post, the motor is arranged on the vertical plate, a rotating shaft is arranged on the motor, the rotating shaft is arranged in parallel with the operating platform, the shell is arranged on the upright post and wraps the rotating shaft, a fixed block is arranged at the top in the shell, a cushion block is arranged at the bottom in the shell, an oil supply interface and an air supply interface are arranged at the top of the shell, an oil return interface is arranged at the bottom of the shell, the fastening ring is arranged on the rotating shaft, the bearing is arranged on the rotating shaft, the bearing is arranged between the fastening ring and the fixed block, the first sealing plate is arranged on one end of the shell through a mounting bolt, the second sealing plate is arranged at the other end of the shell through a mounting bolt, a mounting plate is arranged on the pressure test interface, and the mounting plate is arranged at the top of the shell through the mounting bolt.
2. The high thrust aircraft engine 4 fulcrum bearing seal dynamic test bench of claim 1, characterized in that: the motor is set as a servo motor.
3. The high thrust aircraft engine 4 fulcrum bearing seal dynamic test bench of claim 1, characterized in that: the fastening ring is provided with a connecting block, a clamping block is arranged on the connecting block, and the clamping block is arranged on the fixing block through a mounting bolt.
4. The high thrust aircraft engine 4 fulcrum bearing seal dynamic test bench of claim 1, characterized in that: and the first sealing plate and the second sealing plate are both provided with sealing blocks.
5. The high thrust aircraft engine 4 fulcrum bearing seal dynamic test bench of claim 1 or 4, characterized in that: and the second sealing plate is provided with a connecting ring, and the connecting ring is sleeved on the rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020937820.4U CN212158966U (en) | 2020-05-28 | 2020-05-28 | High thrust aircraft engine 4 fulcrum bearing seal dynamic test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020937820.4U CN212158966U (en) | 2020-05-28 | 2020-05-28 | High thrust aircraft engine 4 fulcrum bearing seal dynamic test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212158966U true CN212158966U (en) | 2020-12-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020937820.4U Expired - Fee Related CN212158966U (en) | 2020-05-28 | 2020-05-28 | High thrust aircraft engine 4 fulcrum bearing seal dynamic test platform |
Country Status (1)
| Country | Link |
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| CN (1) | CN212158966U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115165247A (en) * | 2022-06-30 | 2022-10-11 | 安徽格楠机械有限公司 | Turbofan engine bearing seal dynamic test bench |
-
2020
- 2020-05-28 CN CN202020937820.4U patent/CN212158966U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115165247A (en) * | 2022-06-30 | 2022-10-11 | 安徽格楠机械有限公司 | Turbofan engine bearing seal dynamic test bench |
| CN115165247B (en) * | 2022-06-30 | 2023-08-25 | 安徽格楠机械有限公司 | Dynamic test board for bearing seal of turbofan engine |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201215 |