CN117232851A - High-speed rotor failure test device - Google Patents
High-speed rotor failure test device Download PDFInfo
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- CN117232851A CN117232851A CN202210638473.9A CN202210638473A CN117232851A CN 117232851 A CN117232851 A CN 117232851A CN 202210638473 A CN202210638473 A CN 202210638473A CN 117232851 A CN117232851 A CN 117232851A
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- rotor
- intermediate shaft
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- driving mechanism
- limiting
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- 238000012360 testing method Methods 0.000 title claims abstract description 111
- 230000007246 mechanism Effects 0.000 claims abstract description 97
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- 239000000872 buffer Substances 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 244000126211 Hericium coralloides Species 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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Abstract
The invention discloses a test device for failure of a high-speed rotor, which comprises a driving mechanism, a rotor and a protection mechanism, wherein the protection mechanism comprises an intermediate shaft and a limit bearing matched with the intermediate shaft, and the limit bearing is used for limiting the axial direction of the intermediate shaft; the two ends of the intermediate shaft are respectively connected with the rotor and the driving mechanism, and a first gap is axially arranged between the intermediate shaft and the driving mechanism. After the wheel disc of the rotor breaks or the rotor fails, such as the flying-off of blades of the rotor, a large axial impact load can be generated, the whole rotor moves axially, the impact load is borne by the intermediate shaft and the limiting bearing, meanwhile, the intermediate shaft can move relatively along a small axial range due to the fact that a first gap is arranged between the intermediate shaft and the driving mechanism axially, the intermediate shaft is prevented from directly generating axial impact on the driving mechanism, and therefore the impact load borne by the driving mechanism can be reduced, and equipment damage is reduced.
Description
Technical Field
The invention belongs to the technical field of aero-engine tests, and particularly relates to a test device for high-speed rotor failure.
Background
The wheel disc is one of key rotating parts of the aero-engine and mainly comprises a turbine disc, a compressor disc, a fan disc, a drum barrel and a sealing comb tooth, wherein the drum barrel and the sealing comb tooth are connected with the wheel disc into a whole. The engine strength design algorithm verifies, reduces weight and airworthiness evidence obtaining, rotor over-rotation rupture, wheel disc low cycle fatigue, blade falling, foreign object damage, casing containing and rotor unbalanced response development tests are required to be carried out, so that the rotor is ensured to have enough strength reserve, the wheel disc low cycle life is ensured to meet the requirements, and the engine casing and installation of the engine casing after the blade falling keep structural integrity and cannot cause transmission of excessive vibration force to an aircraft structure.
The test in the prior art is generally carried out on a vertical or horizontal rotary tester, and a test system such as a slip ring primer and the like may be required in the test process, and if rotor failure such as wheel disc breakage, blade flying off and the like occurs in the test process, huge impact load is generated, radial and axial components are contained, the rotor failure is not uniform, and damage is caused to a tester driving system, a transmission system and the slip ring primer which are connected with a test rotor. In order to support the test rotor and reduce vibrations during the test, the tester drive system, transmission system and slip ring primer typically include radial bearings and dampers that cushion a portion of the radial impact load and reduce damage to the equipment, but generally do not have a device that can cushion large axial loads that can cause fatal damage to critical components of the tester drive system and transmission system and precision instruments such as the slip ring primer.
Disclosure of Invention
The invention aims to overcome the defect that in the prior art, the rotor is broken in a high-speed state, and damage is caused by axial impact of rotor failure such as blade flying-off on a test device, and provides a test device for the high-speed rotor failure.
The invention solves the technical problems by the following technical scheme: the test device for the failure of the high-speed rotor comprises a driving mechanism and a rotor, and further comprises a protection mechanism, wherein the protection mechanism comprises an intermediate shaft and a limiting bearing matched with the intermediate shaft, and the limiting bearing is used for limiting the axial direction of the intermediate shaft;
the two ends of the intermediate shaft are respectively connected with the rotor and the driving mechanism, and a first gap is axially arranged between the intermediate shaft and the driving mechanism.
In this scheme, after the rim plate of rotor breaks or rotor such as the blade of rotor flies off and loses efficacy, if produce great axial impact load, the rotor is whole will follow axial displacement, and impact load will be born by jackshaft and spacing bearing, simultaneously because be provided with first clearance along the axial between jackshaft and the actuating mechanism, the jackshaft can follow axial small range relative movement, avoids the jackshaft to directly produce axial impact to actuating mechanism to can reduce the impact load that actuating mechanism received, reduce equipment damage.
Preferably, the test device comprises a test mechanism, the test mechanism is connected with the rotor, and a second gap is axially arranged between the test mechanism and the rotor.
In this scheme, after the rotor became invalid, if produce great axial impact load, the rotor is whole will axial displacement, and the second clearance can provide the surplus to the axial displacement of rotor, avoids directly producing axial impact to testing mechanism, reduces the impact load that testing mechanism received to reduce equipment damage.
Preferably, the test device comprises a test drive shaft through which the test mechanism is connected to the rotor, and the second gap is provided between the test mechanism and the test drive shaft.
In this arrangement, interference of the second gap with the rotor prior to failure can be avoided relative to the placement of the second gap between the rotor and the test drive shaft.
Preferably, the test mechanism is disposed on a side of the rotor opposite the intermediate shaft.
In this scheme, if testing mechanism and jackshaft are in same side, jackshaft department needs extra space to set up testing mechanism, leads to the increase of jackshaft length, sets up testing mechanism and jackshaft respectively in the both sides of rotor for the structure is compacter, simultaneously, owing to avoided jackshaft and test drive shaft to connect in the same side of rotor, is convenient for be connected between testing mechanism and the rotor.
Preferably, the protection mechanism further comprises a limiting disc, the limiting disc is axially mounted on the intermediate shaft, the limiting disc is arranged in the limiting bearing, and a third gap is formed between the limiting disc and the limiting bearing.
In this scheme, when the rotor became invalid, the third clearance provided the surplus for the rotor along axial displacement, reduced the axial impact load of rotor to spacing bearing.
The protection mechanism further comprises a damper, the intermediate shaft is mounted on the damper, and the damper is used for limiting the radial direction of the intermediate shaft.
In the scheme, the damper restrains the radial direction of the rotor, so that the radial impact load of the rotor in failure is buffered, and the radial impact on equipment such as a driving mechanism, a testing mechanism and the like is reduced.
Preferably, the connecting structure between the intermediate shaft and the driving mechanism is a spline, a sleeve tooth or a regular polygon connecting component.
In this scheme, this structure is convenient for transmit the load between drive structure and the jackshaft, simultaneously, when the rotor became invalid, the jackshaft removed along the axial and can not destroy this transmission connection structure to make drive mechanism and jackshaft can carry out many times experiments.
Preferably, the connection structure between the test driving shaft and the test mechanism is a spline, a sleeve tooth or a regular polygon connection assembly.
In this scheme, this structure is convenient for transmit load between testing mechanism and the test drive shaft, simultaneously, when the rotor became invalid, the rotor drove the test drive shaft and along axial displacement can not destroy this transmission connection structure to make testing mechanism and test transmission shaft can carry out many times experiments.
Preferably, the test device comprises a support bearing on which the rotor is mounted.
In the scheme, the supporting bearing restrains the radial direction of the rotor, buffers the radial impact load when the rotor fails, and reduces the radial impact of the rotor on equipment such as a driving mechanism, a testing mechanism and the like.
Preferably, the test device comprises a swing frame on which the support bearing is mounted.
In the scheme, the swing frame can buffer the radial load of the support bearing, and further reduce the radial impact on equipment such as a driving mechanism, a testing mechanism and the like when the rotor fails.
The invention has the positive progress effects that: after the wheel disc of the rotor breaks or the rotor fails, such as the flying-off of blades of the rotor, a large axial impact load can be generated, the whole rotor moves axially, the impact load is borne by the intermediate shaft and the limiting bearing, meanwhile, the intermediate shaft can move relatively along a small axial range due to the fact that a first gap is arranged between the intermediate shaft and the driving mechanism axially, the intermediate shaft is prevented from directly generating axial impact on the driving mechanism, and therefore the impact load borne by the driving mechanism can be reduced, and equipment damage is reduced.
Drawings
FIG. 1 is a schematic structural diagram of a high-speed rotor failure test apparatus according to a preferred embodiment of the present invention.
Description of the reference numerals
Drive mechanism 100
Rotor 200
Test mechanism 300
Test drive shaft 1
Electric primer 2
Mounting base 3
Support bearing 4
Swing frame 5
Base 6
Blade 7
Wheel disc 8
Intermediate shaft 9
Limiting plate 10
Limit bearing 11
Damper 12
Speed change gear box 13
Electric motor 14
First gap 15
Second gap 16
Third gap 17
Spindle 18
Detailed Description
The invention is further illustrated by means of the following examples, which are not intended to limit the scope of the invention.
As shown in fig. 1, the invention discloses a test device for failure of a high-speed rotor, which comprises a driving mechanism 100 and a rotor 200, wherein the test device also comprises a protection mechanism, the protection mechanism comprises an intermediate shaft 9 and a limit bearing 11 matched with the intermediate shaft 9, and the limit bearing 11 is used for limiting the axial direction of the intermediate shaft 9; the rotor 200 and the driving mechanism 100 are connected to both ends of the intermediate shaft 9, and a first gap 15 is provided between the intermediate shaft 9 and the driving mechanism 100 in the axial direction.
Specifically, as shown in fig. 1, the rotor 200 includes the blades 7, the wheel disc 8 and the rotating shaft 18, the intermediate shaft 9 is rigidly connected with the rotating shaft 18, and no axial hard limit is performed between the intermediate shaft 9 and the driving mechanism 100. The drive mechanism 100 includes a speed change gear box 13 and a motor 14, the motor 14 transmitting power to the intermediate shaft 9 through the speed change gear box 13. When the rotor 200 fails, such as the wheel disc 8 breaks or the blades 7 fly off, if a larger axial impact load is generated, the whole rotor 200 moves axially, the impact load is borne by the intermediate shaft 9 and the limiting bearing 11, meanwhile, the intermediate shaft 9 can move relatively along a small axial range due to the first gap 15 arranged between the intermediate shaft 9 and the driving mechanism 100, the intermediate shaft 9 is prevented from directly generating axial impact on the driving mechanism 100, so that the impact load borne by the driving mechanism 100 can be reduced, the equipment damage is reduced, and the test device can be used for a rotor test with larger complete damage or damage risk, such as over-rotation fracture of the rotor of the aeroengine, low cycle fatigue of the wheel disc, blade drop, foreign object damage, casing inclusion, rotor imbalance response and the like.
In this embodiment, as shown in fig. 1, the test apparatus includes a test mechanism 300, the test mechanism 300 is connected to the rotor 200, and a second gap 16 is axially provided between the test mechanism 300 and the rotor 200.
Specifically, as shown in fig. 1, the test mechanism 300 includes a primer 2 and a mounting seat, the primer 2 is mounted on the mounting seat 3, when the rotor 200 fails, if a large axial impact load is generated, the whole rotor 200 will move axially, the second gap 16 can provide a margin for the axial movement of the rotor 200, so that the axial impact on the test mechanism 300 is avoided, and the impact load on the test mechanism 300 is reduced, thereby reducing the damage to equipment.
As shown in fig. 1, the test apparatus includes a test drive shaft 1, a test mechanism 300 is connected to the rotor 200 through the test drive shaft 1, and a second gap 16 is provided between the test mechanism 300 and the test drive shaft 1. Of course, in other embodiments, the second gap 16 may also be provided between the test drive shaft 1 and the rotor 200.
Specifically, as shown in fig. 1, one end of the test driving shaft 1 is fixedly connected with the rotating shaft 18 of the rotor 200, the other end is connected with the current collector 2, and the second gap 16 is arranged between the test driving shaft 1 and the current collector 2, so that interference of the second gap 16 on the rotor 200 before failure can be avoided relative to arranging the second gap 16 between the rotor 200 and the test driving shaft 1.
As shown in fig. 1, the test mechanism 300 is provided on the side of the rotor 200 opposite to the intermediate shaft 9. Of course, in other embodiments, the testing mechanism 300 and the intermediate shaft 9 may be disposed on the same side of the rotor 200, such as a vertical rotation tester, where the rotor 200 is usually in a cantilever support state, and if the testing mechanism 300 and the intermediate shaft 9 are disposed on the same side, additional space is required at the intermediate shaft 9 to dispose the testing mechanism 300, resulting in an increase in the length of the intermediate shaft 9, and thus, the testing mechanism 300 is usually disposed on the opposite side of the rotor 200 from the intermediate shaft 9, i.e., the side far from the connection of the rotor and the output shaft of the speed change gearbox 13.
As shown in fig. 1, the protection mechanism further includes a limiting disc 10, the limiting disc 10 is fixedly installed on the intermediate shaft 9 along the axial direction, the limiting disc 10 is disposed in the limiting bearing 11, and a third gap 17 is disposed between the limiting disc 10 and the limiting bearing 11, so that the limiting disc 10 has an axial activity allowance in the limiting bearing 11. Before the rotor 200 fails, the support bearing 4 and the swing frame 5 axially position the rotor 200; the third gap 17 provides a margin for axial movement of the rotor 200 when the rotor 200 fails to reduce axial impact loading of the rotor 200 on the drive mechanism 100.
As shown in fig. 1, the protection mechanism further includes a damper 12, and the intermediate shaft 9 is mounted on the damper 12, and the damper 12 is used for limiting the radial direction of the intermediate shaft 9. The damper 12 restrains the radial direction of the rotor 200, thereby buffering the radial impact load when the rotor 200 fails, and reducing the radial impact to the driving mechanism 100, the testing mechanism 300, and other devices. In this embodiment, the limit bearing 11 is closer to the rotor than the damper 12, however, in other embodiments, the damper 12 may be closer to the rotor 200 than the limit bearing 11, so that the radial impact load when the rotor 200 fails may be better buffered.
In this embodiment, the connection structure between the intermediate shaft 9 and the driving mechanism 100 is a spline, and in other embodiments, the connection structure may be a socket tooth or a regular polygon connection assembly. The above-described connection structure facilitates load transfer between the drive structure and the intermediate shaft 9, and at the same time, when the rotor 200 fails, the intermediate shaft 9 moves in the axial direction without breaking the transmission connection structure, thereby enabling the drive mechanism 100 and the intermediate shaft 9 to perform a plurality of tests.
Likewise, the connection structure between the test driving shaft 1 and the test mechanism 300 is a spline, however, in other embodiments, the connection structure may be a socket or a regular polygon connection assembly, and the connection structure facilitates the load transmission between the test mechanism 300 and the test driving shaft 1, and at the same time, when the rotor 200 fails, the rotor 200 drives the test driving shaft 1 to move along the axial direction without breaking the transmission connection structure, so that the test mechanism 300 and the test driving shaft can perform multiple tests.
As shown in fig. 1, the test apparatus includes a support bearing 4, and a rotor 200 is mounted on the support bearing 4. The support bearing 4 restrains the radial direction of the rotor 200, buffers the radial impact load when the rotor 200 fails, and reduces the radial impact of the rotor 200 on the driving mechanism 100, the testing mechanism 300 and other devices.
As shown in fig. 1, the test apparatus includes a swing frame 5, and a support bearing 4 is mounted on the swing frame 5.
Specifically, as shown in fig. 1, the rotor 200 is supported by a pair of support bearings 4, a swing frame 5 and a base 6, and the swing frame 5 can buffer the radial load of the support bearings 4, so as to further reduce the radial impact on the driving mechanism 100, the testing mechanism 300 and other devices when the rotor 200 fails.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (10)
1. The test device for the failure of the high-speed rotor comprises a driving mechanism and the rotor, and is characterized by further comprising a protection mechanism, wherein the protection mechanism comprises an intermediate shaft and a limiting bearing matched with the intermediate shaft, and the limiting bearing is used for limiting the axial direction of the intermediate shaft;
the two ends of the intermediate shaft are respectively connected with the rotor and the driving mechanism, and a first gap is axially arranged between the intermediate shaft and the driving mechanism.
2. A high speed rotor failure test apparatus as recited in claim 1, wherein the test apparatus includes a test mechanism coupled to the rotor, a second gap being provided axially between the test mechanism and the rotor.
3. A high speed rotor failure test apparatus as recited in claim 2, wherein the test apparatus includes a test drive shaft through which the test mechanism is coupled to the rotor, the second gap being disposed between the test mechanism and the test drive shaft.
4. A high speed rotor failure test apparatus as claimed in claim 2, wherein the test mechanism is disposed on a side of the rotor opposite the intermediate shaft.
5. The high-speed rotor failure test device according to claim 1, wherein the protection mechanism further comprises a limiting disc, the limiting disc is axially mounted on the intermediate shaft, the limiting disc is arranged in the limiting bearing, and a third gap is arranged between the limiting disc and the limiting bearing.
6. The high speed rotor failure test apparatus of claim 1, wherein the protection mechanism further comprises a damper, the intermediate shaft being mounted on the damper, the damper being configured to limit a radial direction of the intermediate shaft.
7. The high-speed rotor failure test apparatus of claim 1, wherein the connection structure between the intermediate shaft and the drive mechanism is a spline, a socket tooth, or a regular polygon connection assembly.
8. A high speed rotor failure test apparatus as recited in claim 3, wherein the connection between the test drive shaft and the test mechanism is a spline, a socket tooth, or a regular polygon connection assembly.
9. A high speed rotor failure test apparatus as claimed in any one of claims 1 to 8, wherein the test apparatus includes a support bearing on which the rotor is mounted.
10. A high speed rotor failure test apparatus as recited in claim 9, wherein the test apparatus includes a swing frame, the support bearing being mounted on the swing frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210638473.9A CN117232851A (en) | 2022-06-07 | 2022-06-07 | High-speed rotor failure test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210638473.9A CN117232851A (en) | 2022-06-07 | 2022-06-07 | High-speed rotor failure test device |
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| Publication Number | Publication Date |
|---|---|
| CN117232851A true CN117232851A (en) | 2023-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210638473.9A Pending CN117232851A (en) | 2022-06-07 | 2022-06-07 | High-speed rotor failure test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118768714A (en) * | 2024-09-12 | 2024-10-15 | 安徽万宇机械设备科技有限公司 | Friction stir additive manufacturing device and control method |
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2022
- 2022-06-07 CN CN202210638473.9A patent/CN117232851A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118768714A (en) * | 2024-09-12 | 2024-10-15 | 安徽万宇机械设备科技有限公司 | Friction stir additive manufacturing device and control method |
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