CN114441795A - Airplane generator rotor overspeed testing device and method - Google Patents
Airplane generator rotor overspeed testing device and method Download PDFInfo
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- CN114441795A CN114441795A CN202111619921.2A CN202111619921A CN114441795A CN 114441795 A CN114441795 A CN 114441795A CN 202111619921 A CN202111619921 A CN 202111619921A CN 114441795 A CN114441795 A CN 114441795A
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- 238000012360 testing method Methods 0.000 title claims abstract description 79
- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000001816 cooling Methods 0.000 claims abstract description 72
- 238000010008 shearing Methods 0.000 claims abstract description 10
- 238000005461 lubrication Methods 0.000 claims abstract description 9
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 239000000110 cooling liquid Substances 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 240000005002 Erythronium dens canis Species 0.000 claims 1
- 238000010998 test method Methods 0.000 claims 1
- 230000001050 lubricating effect Effects 0.000 abstract description 5
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 83
- 239000010720 hydraulic oil Substances 0.000 description 4
- 230000000903 blocking effect Effects 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 239000000306 component Substances 0.000 description 2
- 239000008358 core component Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
- G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the technical field of high-speed testing of rotors, and provides an overspeed testing device and method for an aircraft generator rotor, wherein the device comprises an input spline shaft, an upper shell, a lower shell, a tested rotor and a cooling oil way; the tested rotor is horizontally placed in a sealed space formed by the upper shell and the lower shell; the cooling oil circuit is used for providing cooling and lubrication for bearings at two ends of the tested rotor; one end of the input spline shaft is connected with the dragging table at the power input end, the other end of the input spline shaft is connected with the tested rotor, and the middle part of the input spline shaft is provided with an overload shearing point. The driving end of the invention adopts a spline meshing form, which can ensure good coaxiality and stable transmission of input torque without impact on equipment; the independent lubricating and cooling oil circuit is designed in the testing device, so that the lubrication and cooling of the supporting bearings at the two ends can be greatly improved, the service life of the bearing is prolonged, and the safe and reliable performance of the testing process is ensured.
Description
Technical Field
The invention relates to the technical field of high-speed rotor testing, in particular to an overspeed testing device and method for an aircraft generator rotor, which are used for realizing failure verification of the aircraft generator rotor in a high-speed state.
Background
The civil aircraft generator is an important component of an aircraft power supply system, is arranged on a gear box of an aircraft engine, and converts mechanical power output by the engine into electric power required by various loads on the aircraft. The aircraft generator is an electrical product with a complex structure and mainly comprises a permanent magnet exciter, an alternating current exciter, a main generator, a pump system for cooling and the like; the core component rotor of the main generator is always in a high-speed rotating state in a normal power generation state, and the failure of the core component rotor usually causes great destructive damage to the body of the aircraft generator, and finally causes the aircraft generator to be switched off and shut down, so that the redundancy of an aircraft power supply system is reduced.
At the present stage, the manufacturer or supplier of the aircraft requires the rotor inside it to perform an overspeed test in case of newly installed or repaired and reinstalled windings, the rotational speed of the overspeed test being divided into three levels, 12000 rpm, 24000 rpm and 30000 rpm respectively, to verify whether the rotor fails at different rotational speeds. For the overspeed test of rotor, there is dedicated testing arrangement abroad at present, it mainly hangs the high-speed rotation of motor drive rotor with the rotor, but there is certain defect in the use in this kind of mounting means, and the connection of rotor and testing arrangement drive shaft is fixed for the rigidity crimping, can lead to motor drive shaft and rotor shaft disalignment like this to make the irregular motion appear in the rotor under the high-speed rotatory condition, can lead to the rotor to break away from the pin joint departure at last, damage testing arrangement and tested piece. For domestic rotor overspeed testing arrangement, mainly adopt horizontal open type to place, its shortcoming mainly has: the rotor is not provided with a protective cover when rotating at high speed, and is lack of safety protection; the cooling mode of the support bearing is air cooling, the heat dissipation efficiency is not high, and the rotating speed of the rotor cannot be too high; the connection mode of the coupler has no failure overload protection function.
Disclosure of Invention
The invention aims to overcome at least one of the defects of the prior art, and provides a device and a method for testing the overspeed of a rotor of an aircraft generator, which greatly improve the heat dissipation performance of a bearing and prolong the service life of the bearing. Moreover, the scheme has the advantages of compact structure, convenient installation and labor saving.
The invention adopts the following technical scheme:
on one hand, the invention provides an overspeed testing device for an aircraft generator rotor, which comprises an input spline shaft, an upper shell, a lower shell, a tested rotor and a cooling oil way, wherein the input spline shaft is arranged on the upper shell;
the tested rotor is horizontally placed in a sealed space formed by the upper shell and the lower shell;
the cooling oil path is used for providing cooling and lubrication for bearings at two ends of the tested rotor;
one end of the input spline shaft is connected with the dragging table at the power input end, the other end of the input spline shaft is connected with the tested rotor, and the middle part of the input spline shaft is provided with an overload shearing point.
There is further provided in accordance with any of the possible implementations described above an implementation in which the rotor under test includes a first end and a second end, the first end having a self-contained first bearing and a first bearing seat; the first end of the rotor under test is mounted within the upper housing by the first bearing and a first bearing seat;
a second bearing seat is arranged in the lower shell, and a support bearing is arranged in the second bearing seat; the support bearing is for supporting the second end of the rotor under test.
And a supporting bearing at the second end of the tested rotor axially fixes the rotor through a bearing retainer ring of the rotor, the bearing retainer ring is connected with the lower shell through bolts, and bolt holes are reserved in the lower shell and used for connecting the bearing retainer ring with the lower shell.
Any one of the above possible implementation manners further provides an implementation manner, and the apparatus further includes a vibration sensor disposed at the second end of the tested rotor, and the vibration sensor is in wireless or wired signal connection with the detection system.
In any of the above possible implementations, there is further provided an implementation in which the cooling oil passage is provided in the side walls of the upper casing and the lower casing, and the cooling oil passes through the cooling oil passage to reach the support bearing and the first bearing, and cools and lubricates the support bearing and the first bearing by injection.
In any of the above possible implementation manners, there is further provided an implementation manner that cooling oil first reaches the support bearing at the second end of the tested rotor through cooling oil passages provided in the side walls of the upper casing and the lower casing, so as to cool and lubricate the support bearing; the cooling oil then reaches the first bearing at the first end of the tested rotor through a separate cooling oil path arranged in the center of the tested rotor, and the first bearing is cooled and lubricated. This cooling oil circuit design utilizes the inside independent cooling oil circuit of the rotor that is tested, reduces the unnecessary operation of punching, more is favorable to guaranteeing oil pressure and oil mass with an oil circuit.
Any one of the above possible implementation manners further provides an implementation manner that the input spline shaft is connected with the input shaft of the traction table in a gear meshing manner, and the input spline shaft is connected with the rotor to be tested in a dog meshing manner.
In any of the above possible implementation manners, there is further provided an implementation manner that the rotor under test is fixedly connected with the lower housing through a self-contained bearing retainer ring thereof, so as to limit the axial displacement of the rotor under test.
In any of the above possible implementations, there is further provided an implementation in which the upper housing and the lower housing are fixedly connected by screws.
Any of the above possible implementations further provides an implementation, and the upper housing is fixed to the dragging table flange by fitting the mounting flange.
In another aspect, the present invention also provides a method for testing the overspeed of a rotor of an aircraft generator, the method using the apparatus described above, the method comprising:
s1, mounting the device on a flange plate of a dragging table, and connecting cooling liquid circulating equipment of the dragging table to a cooling oil path of the device;
s2, starting the test, setting different rotating speeds for the dragging table, and transmitting torque to the tested rotor by the dragging table through the input spline shaft to drive the tested rotor to rotate at a high speed; meanwhile, cooling oil cools and lubricates the support bearing and the first bearing through the cooling oil way; then the cooling oil is pumped out to a dragging table to finish cooling and temperature reduction, and the oil is continuously recycled until overspeed tests of all rotation speed grades are finished;
s3, detecting the vibration of the tested rotor by a vibration sensor arranged at the second end of the tested rotor, and stopping the machine for protection in real time when the vibration amplitude exceeds an allowable value; if the bearing of the tested rotor fails due to emergency overload, the input spline shaft is cut off through the overload protection point, and the safety and reliability of the test are ensured.
In any of the above possible implementation manners, there is further provided an implementation manner that, in step S2, the rotation speed levels are three levels, which are 12000 rpm, 24000 rpm, and 30000 rpm, respectively.
The invention has the beneficial effects that:
due to the adoption of the technical scheme, the two ends of the tested rotor are horizontally arranged and installed in a closed manner, so that good coaxiality and safety can be ensured; the bearings at the two ends adopt an oil spraying cooling and lubricating mode, so that the heat dissipation performance of the bearings is greatly improved, and the service life of the bearings is prolonged. Moreover, the scheme has the advantages of compact structure, convenience in installation, manpower saving and capability of rapidly completing the arrangement of the testing device. In order to improve the safety level of the testing device, the overload shearing function of the input spline shaft is designed, whether the vibration value of the testing device exceeds an allowable value or not is monitored in the testing process, and if the vibration value exceeds the allowable value, the driving end can be shut down for protection in real time. In addition, the present invention is expected to obtain considerable test revenue each year if it can land effectively.
Drawings
Fig. 1 is a schematic perspective view of an overspeed testing device for an aircraft generator rotor according to an embodiment of the present invention.
Fig. 2 is a schematic view (partially cut) of the overall structure of the embodiment.
Fig. 3 is a schematic top view of the overall structure of the embodiment.
Fig. 4 is a right-view schematic diagram showing the overall structure of the embodiment.
Fig. 5 is a schematic view of a cooling oil path in the embodiment.
FIG. 6 is a schematic structural view of the input spline shaft in the embodiment.
In the figure, 1-input spline shaft; 2-oil blocking of an oil outlet; 3-upper shell; 4-a lower shell; 5-fixing bolts (8); 6-oil inlet oil blocking; 7-a second bearing block; 8-a support bearing; 9-the rotor under test; 10-cooling oil circuit; 11-installing a fixing hole; 12-an oil inlet; 13-an oil outlet; 14-a key slot hole; 15-oil outlet; and 16-oil feeding port.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that technical features or combinations of technical features described in the following embodiments should not be considered as being isolated, and they may be combined with each other to achieve better technical effects. In the drawings of the embodiments described below, the same reference numerals appearing in the respective drawings denote the same features or components, and may be applied to different embodiments.
Aiming at the problem of overspeed test of the rotor of the existing aircraft generator, the embodiment of the invention provides a device for overspeed test of the rotor of the aircraft generator, and the key technology of the device is as follows: the tested rotor 9 is horizontally placed and installed in a closed mode in the testing process, the supporting mode is that bearings at two ends are supported, the cooling mode of the bearings is oil spraying cooling, and the driving end is connected with the rotor and designed to be connected with a special spline shaft. When performing a rotor overspeed test: the rotor is required to be installed in a testing device firstly, and then the rotor and the testing device are integrally installed on a dragging table; the cooling oil circulating equipment on the dragging table is connected, so that the bearings at the two ends of the rotor can be cooled in real time; meanwhile, a vibration sensor is required to be arranged on the testing device, and when the high-speed running vibration value of the rotor exceeds a specified value, the dragging table can be stopped in time; in addition, for the rotor rotation failure blocking under the extreme condition, the spline shaft connecting the dragging table and the rotor end is designed with overload protection, and can be cut off in time, so that the safety protection of equipment and personnel is realized.
As shown in fig. 1-4, the overspeed testing device for the rotor of the aircraft generator according to the embodiment of the invention comprises an input spline shaft 1, an upper shell 3, a lower shell 4, a tested rotor 9 and a cooling oil path 10; the rotor 9 to be tested is horizontally placed in the sealed space formed by the upper shell 3 and the lower shell 4; the cooling oil path 10 is used for providing cooling and lubrication for bearings at two ends of the tested rotor 9; one end of the input spline shaft 1 is connected with a dragging table at the power input end, the other end of the input spline shaft is connected with the tested rotor 9, and an overload shearing point is arranged in the middle of the input spline shaft 1.
In a specific embodiment, in order to reduce the weight, the flange of the upper housing 3 is designed by removing materials, meanwhile, 8 mounting fixing holes 11 are drilled on the mounting flange of the upper housing 3, the mounting fixing holes 11 are used for matching with the flange of the dragging table to fix the overspeed testing device, 1 positioning hole 14, 1 oil inlet 12 and 1 oil outlet 13 are also needed to be drilled, 1 threaded hole for mounting the oil plug 2 of the oil outlet is reserved in the side edge of the flange, and the key slot hole 14 is used for mounting and positioning the whole testing device.
In a specific embodiment, the upper housing 3 and the lower housing 4 are connected together by fixing bolts 5; the second bearing block 7 is fixedly connected with the lower shell 4 through a screw; the tested rotor 9 is fixedly connected with the lower shell 4 through a bearing retainer ring (not shown) of the tested rotor 9, and the axial displacement of the tested rotor 9 is limited.
In a specific embodiment, the upper housing 3 and the lower housing 4 are connected together by 8 fixing bolts 5, a cooling oil path 10 is designed on the side wall of the upper housing 3, a cooling oil path 10 is designed on the side wall and the bottom of the lower housing 4, an upper oil port 16 and a lower oil port 15 are designed at the tail end of the cooling oil path 10 of the lower housing 4, the upper oil port 16 is used for lubricating and cooling the supporting bearing 8, and the lower oil port 15 is used for lubricating and cooling a cylindrical bearing, namely a first bearing, on the other side of the tested rotor 9; the lower shell 4 is designed with a structure specially used for mounting the second bearing seat 7, and the second bearing seat 7 is fastened and connected with the lower shell 4 through screws.
In one embodiment, the supporting bearing 8 is installed in the second bearing seat 7, and supports the second end of the tested rotor 9, and the first end of the tested rotor 9 is installed at the first bearing seat support of the upper shell 3 (note: the tested rotor 9 is provided with the first bearing and the first bearing seat by itself); in addition, a threaded hole for installing the oil plug 6 of the oil inlet is reserved on the outer side of the lower shell 4.
In one embodiment, the cooling oil path 10 is separately designed by the upper shell 3 and the lower shell 4, the cooling oil flows in from the oil path of the upper shell 3 and is transmitted to the bottom of the second bearing seat 7 (the anti-driving end bearing seat) through the oil path of the lower shell 4, the cooling and lubrication of the first bearing (the driving end bearing) are realized through the lower oil port 15 of the lower shell 4, and the cooling and lubrication of the supporting bearing 8 (the anti-driving end bearing) are realized through the upper oil port 16 of the lower shell 4. As shown in fig. 5, the oil inlet oil plug 6 is mounted on the lower housing 4; the oil outlet oil plug 2 is arranged on the upper shell 3.
The cooling oil path 10 can be flexibly arranged, and in another embodiment, the cooling oil path 10 is only arranged in the side walls of the upper shell 3 and the lower shell 4, and the cooling oil respectively reaches the supporting bearing 8 and the first bearing.
In one embodiment, the rotor 9 to be tested is in spline engagement with the input spline shaft 1, the connection between the input spline shaft 1 and the rotor 9 to be tested is in clearance fit, and the middle part of the input spline shaft 1 is designed with an overload protection function, for example, an overload shearing point can be designed, and the cross-sectional diameter at the overload shearing point is smaller than that of other areas of the input spline shaft 1, as shown in fig. 6. Under the emergency overload condition, the input spline shaft 1 can be sheared in an overload mode, and safe and reliable operation of the equipment can be guaranteed to a certain extent. The diameter of the overload shearing point is determined through experiments or calculation, and when the load at the overload shearing point exceeds a critical value, the input spline shaft can be automatically subjected to overload shearing.
In a specific embodiment, the other end of the input spline shaft 1 is connected with an input shaft of a dragging table, the dragging table is provided with a special hydraulic oil cooling system, before a test is executed, an oil inlet/outlet channel of the oil cooling system needs to be installed to a installing flange of the dragging table, a vibration sensor needs to be installed to a reverse driving end (for example, the second end of a tested rotor 9) of the testing device, the vibration sensor adopts an adhesive mode, then different speed grades are set on an operation interface of the dragging table, the dragging table is started to execute an overspeed test, at the moment, the dragging table drives the input spline shaft 1 and the tested rotor 9 to rotate at a high speed, the oil cooling system outside the dragging table synchronously starts to work to complete the lubrication and cooling of supporting bearings at two ends inside the testing device, and the lubricated and cooled hydraulic oil can be concentrated at the bottom of an inner cavity formed by the upper shell 3 and the lower shell 4, and then the hydraulic oil is pumped to an external heat exchanger through a dragging table cooling oil pump to finish cooling of the hydraulic oil. If the vibration value detected by the vibration sensor of the dragging table exceeds the allowable value in the test process, the dragging table can be immediately shut down for protection, and the safety of personnel and equipment is ensured.
The embodiment of the invention discloses a method for testing overspeed of a rotor of an aircraft generator, which specifically comprises the following steps:
and S1, mounting an overspeed testing device on the flange plate of the dragging table, and connecting cooling circulation equipment of the dragging table to an oil inlet and an oil outlet on the flange plate.
S2, after the test is started, different rotating speeds are set on the operation interface of the dragging table, the dragging table transmits torque to the tested rotor 9 through the input spline shaft 1 to drive the tested rotor 9 to rotate at high speed, and when the tested rotor 9 rotates, and a cooling oil pump of the dragging table is also started simultaneously, cooling oil is continuously pumped into oil inlet oil paths 10 of the upper shell 3 and the lower shell 4 through an oil inlet 12, finally the cooling oil is sprayed through an upper oil port 16 of the oil inlet oil path 10 to lubricate a supporting bearing 8, a lower oil port 15 of the oil inlet oil path 10 is sprayed through an oil path of an inner cavity of the tested rotor 9 to lubricate a first bearing arranged on the other side of the tested rotor, the oil after cooling the bearing is pumped out to a heat exchanger of a cooling system of the dragging table through an oil outlet 13 to complete cooling, and the oil is continuously recycled until overspeed tests of all rotation speed grades are completed.
S3, before testing, a vibration sensor is mounted to a reverse driving end, namely a second end, of the overspeed testing device, and a collecting channel on the dragging table can complete vibration monitoring of the testing device in real time; when the vibration amplitude exceeds an allowable value, real-time shutdown protection is carried out; if the bearing of the tested rotor 9 fails due to emergency overload, the input spline shaft 1 is sheared through an overload protection point, and the safety and reliability of the test are ensured.
The invention has the innovation that the horizontally placed closed overspeed testing device is provided, and the driving end adopts a spline meshing form, so that good coaxiality and stable transmission of input torque can be ensured, and no impact is caused on equipment; the independent lubricating and cooling oil circuit is designed in the testing device, so that the lubrication and cooling of the supporting bearings at the two ends can be greatly improved, the service life of the bearing is prolonged, and the safe and reliable performance of the testing process is ensured. In addition, the vibration value monitoring of the testing equipment is introduced, so that the safety of personnel and equipment can be further improved.
While several embodiments of the present invention have been presented herein, it will be appreciated by those skilled in the art that changes may be made to the embodiments described herein without departing from the spirit of the invention. The above examples are merely illustrative and should not be taken as limiting the scope of the invention.
Claims (10)
1. The overspeed testing device for the rotor of the aircraft generator is characterized by comprising an input spline shaft, an upper shell, a lower shell, a tested rotor and a cooling oil way;
the tested rotor is horizontally placed in a sealed space formed by the upper shell and the lower shell;
the cooling oil path is used for providing cooling and lubrication for bearings at two ends of the tested rotor;
one end of the input spline shaft is connected with the dragging table at the power input end, the other end of the input spline shaft is connected with the tested rotor, and the middle part of the input spline shaft is provided with an overload shearing point.
2. An aircraft generator rotor overspeed testing apparatus as set forth in claim 1, wherein said rotor under test includes a first end and a second end, said first end having a self-contained first bearing and a first bearing seat; the first end of the rotor under test is mounted within the upper housing by the first bearing and a first bearing seat;
a second bearing seat is arranged in the lower shell, and a support bearing is arranged in the second bearing seat; the support bearing is for supporting the second end of the rotor under test.
3. An aircraft generator rotor overspeed testing apparatus as set forth in claim 2, further comprising a vibration sensor disposed at a second end of said rotor under test.
4. An aircraft generator rotor overspeed testing apparatus as set forth in claim 2, wherein said cooling oil path is provided in a side wall of said upper and lower housings, and cooling oil is passed through said cooling oil path to and cools and lubricates said support bearing and said first bearing by means of injection.
5. An aircraft generator rotor overspeed testing device as claimed in claim 1, wherein said input spline shaft is connected with a traction table input shaft by gear engagement, and said input spline shaft is connected with said rotor under test by dog-tooth engagement.
6. The aircraft generator rotor overspeed testing apparatus of claim 1, wherein said rotor under test is fixedly connected to said lower housing by its own retaining ring, limiting axial displacement of said rotor under test.
7. An aircraft generator rotor overspeed testing apparatus of claim 1 wherein said upper housing and said lower housing are fixedly attached by screws.
8. An aircraft generator rotor overspeed testing apparatus as in any one of claims 1 to 7 wherein said upper housing is secured in place by a mounting flange engaging a drive-train-table flange.
9. A method of testing aircraft generator rotor overspeed using the apparatus of any one of claims 1 to 8, the method comprising:
s1, mounting the device on a flange plate of a dragging table, and connecting cooling liquid circulating equipment of the dragging table to a cooling oil path of the device;
s2, starting the test, setting different rotation speed grades for the dragging table, and transmitting torque to the tested rotor by the dragging table through the input spline shaft to drive the tested rotor to rotate at a high speed; meanwhile, cooling oil cools and lubricates the support bearing and the first bearing through the cooling oil way; then the cooling oil is pumped back to the dragging table by a pump to finish cooling and temperature reduction, and the oil is continuously recycled until overspeed tests of all rotation speed grades are finished;
s3, detecting the vibration of the tested rotor by a vibration sensor arranged at the second end of the tested rotor, and stopping the machine for protection in real time when the vibration amplitude exceeds an allowable value; if the bearing of the tested rotor fails due to emergency overload, the input spline shaft is cut off through the overload protection point, and the safety and reliability of the test are ensured.
10. An aircraft generator rotor overspeed testing method according to claim 9, wherein in step S2, the rotation speed is three-level, 12000 rpm, 24000 rpm, 30000 rpm respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111619921.2A CN114441795A (en) | 2021-12-27 | 2021-12-27 | Airplane generator rotor overspeed testing device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111619921.2A CN114441795A (en) | 2021-12-27 | 2021-12-27 | Airplane generator rotor overspeed testing device and method |
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| Publication Number | Publication Date |
|---|---|
| CN114441795A true CN114441795A (en) | 2022-05-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111619921.2A Pending CN114441795A (en) | 2021-12-27 | 2021-12-27 | Airplane generator rotor overspeed testing device and method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116754197A (en) * | 2023-06-13 | 2023-09-15 | 小米汽车科技有限公司 | Motor rotor's test system |
Citations (3)
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|---|---|---|---|---|
| WO2009004956A1 (en) * | 2007-07-05 | 2009-01-08 | Toyota Jidosha Kabushiki Kaisha | Unbalance correcting device for high-speed rotating machine |
| CN105510044A (en) * | 2015-12-31 | 2016-04-20 | 苏州东菱科技有限公司 | High-speed rotor blade flying-off test device and test method |
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2021
- 2021-12-27 CN CN202111619921.2A patent/CN114441795A/en active Pending
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|---|---|---|---|---|
| WO2009004956A1 (en) * | 2007-07-05 | 2009-01-08 | Toyota Jidosha Kabushiki Kaisha | Unbalance correcting device for high-speed rotating machine |
| CN105510044A (en) * | 2015-12-31 | 2016-04-20 | 苏州东菱科技有限公司 | High-speed rotor blade flying-off test device and test method |
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| Title |
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| 黄金平 等: ""涡轮泵滚动轴承－转子系统高速运行试验研究"", 《火箭推进》, vol. 46, no. 2, 30 April 2020 (2020-04-30), pages 50 - 56 * |
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| CN116754197A (en) * | 2023-06-13 | 2023-09-15 | 小米汽车科技有限公司 | Motor rotor's test system |
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