CN106989925A - Aero-engine high-speed bearing tests radial loading device - Google Patents
Aero-engine high-speed bearing tests radial loading device Download PDFInfo
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- CN106989925A CN106989925A CN201710408739.XA CN201710408739A CN106989925A CN 106989925 A CN106989925 A CN 106989925A CN 201710408739 A CN201710408739 A CN 201710408739A CN 106989925 A CN106989925 A CN 106989925A
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- spacer ring
- bearing
- load bearings
- ring
- load
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
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- General Physics & Mathematics (AREA)
- Rolling Contact Bearings (AREA)
- Support Of The Bearing (AREA)
Abstract
The present invention proposes a kind of aero-engine high-speed bearing experiment radial loading device, including：Test axle, two load bearings, the first spacer ring and the second spacer ring and loading axis bearing；Testing axle two ends is respectively used to connect a test bearing；Two load bearings are the angular contact ball bearing of back-to-back configuration, and the inner ring of two load bearings is fixedly installed on the middle part for testing axle；First spacer ring and the second spacer ring are arranged between two load bearings, and the end face close to the first spacer ring side of second spacer ring, which is provided with multiple blind holes, the blind hole, is provided with spring；The outer ring that the spring contacts with the first spacer ring and promotes first spacer ring and the second spacer ring to extrude two load bearings respectively, to apply axial load to the outer ring；Load bearings cover for seat is located at the outer ring of two load bearings.Load bearings can select suitable goods shelf productses, and the course of work is reliable and stable, does not result in the problem of roller departs from.
Description
Technical field
The present invention relates to a kind of experimental rig for applying radial load to bearing, more particularly to a kind of aero-engine is at a high speed
Bearing test radial loading device.
Background technology
Rolling bearing is one of core component of aero-engine, the characteristics of with high speed, high temperature, high reliability, if
Bearing breaks down, and will influence service life of aeroengine, or even jeopardizes personal safety, thus must carry out the bearing examination of correlation
Test.For the loading conditions of simulation bearing on the engine, high-speed bearing needs to apply radial load at the trial.Current bearing test
The most frequently used load mode is hydraulic loaded, i.e., radial loading device is loaded using hydraulic jack, pass through radial loaded
Load bearings in device are by radial load transfer to test bearing.During bearing test, experiment axle typically uses simple beam structure,
I.e. test bearing is two ends fulcrum, and radial loading device is located at the center of two test bearings, it is ensured that the test bearing institute at two ends
The radial load received is equal, and the half of the load suffered by loading device.
Existing high-speed bearing experiment radial loading device generally comprises bearing block, load bearings, gland, spacer sleeve, spiral shell
The parts such as bolt, load bearings are using single set or two sets of roller bearings.The effect of bearing block is to install load bearings and will load
The radial load that oil cylinder applies passes to load bearings.The effect of load bearings is that by testing axle the static(al) of oil cylinder is delivered into rotation
The test bearing turned.The effect of the parts such as gland, spacer sleeve, bolt is that load bearings are positioned and fastened.
Existing radial loading device has the following disadvantages：
1st, because load bearings are roller bearing, it can be free to move axially between the outer ring of bearing and inner ring, and loading
The circumference of device can not fasten (loading force can not pass to load bearings if fastening), therefore loading device has axial direction and week
To two frees degree (the circumferential free degree does not influence experiment).Deposited when there is certain convexity and installation due to roller between bearing and axle
In malalignment so that when to loading roller bearing apply radial load when easily produce it is crooked, this phenomenon experiment axle at a high speed
Rotation performance is especially prominent, and load bearings can be caused to occur beat, causes whole loading device (to contain load bearings, middle spacer sleeve
Deng) vibration is big, and then cause rotor oscillation to increase, influence process of the test.Occurred when serious the rollers of load bearings completely from
The phenomenon departed from inner track, causes load cylinder piston rod top to the experiment axle of high speed rotation, causes experiment not enter
OK, or even destructive test equipment.
2nd, load bearings performance requirement is high, chooses difficult.It must is fulfilled for following condition：Rated speed turns not less than experiment
Speed；Bearing capacity need to be more than test bearing (during single set load bearings, load be test bearing load twice)；Internal diameter need to be more than
The internal diameter (otherwise can not install) of test bearing.From the point of view of conditions above, the performances of load bearings (speed capability, bearing capacity,
Dn values etc.) test bearing need to be higher than, and condition of work is more severe (outer ring is supported without fixed).Come for high-speed bearing experiment
Say, the condition of work of some test bearings is close to the performance boundary of prior art lower bearing, therefore the selection of load bearings is non-
It is often difficult.Often occur the situation of load bearings damage in process of the test, have a strong impact on experiment progress.
Above- mentioned information is only used for strengthening the understanding of the background to the present invention, therefore it disclosed in the background section
It can include not constituting the information to prior art known to persons of ordinary skill in the art.
The content of the invention
It is an object of the invention to overcome above-mentioned the deficiencies in the prior art, there is provided stable and reliable in work, the easy selection of one kind
The aero-engine high-speed bearing experiment radial loading device of load bearings.
The additional aspect and advantage of the present invention will be set forth in part in the description, and partly will be from description
It is apparent from, or can the acquistion by the practice of the present invention.
According to an aspect of the present invention, a kind of aero-engine high-speed bearing experiment radial loading device, including：Experiment
Axle, two load bearings, the first spacer ring and the second spacer ring and loading axis bearing；Testing axle two ends is respectively used to connect an experiment axle
Hold；Two load bearings are the angular contact ball bearing of back-to-back configuration, and the inner ring of two load bearings is fixed and set
It is placed in the middle part of the experiment axle；First spacer ring and the second spacer ring are arranged between two load bearings, described second every
The end face close to the first spacer ring side of circle, which is provided with multiple blind holes, the blind hole, is provided with spring；The spring and first every
Circle contacts and promotes first spacer ring and the second spacer ring to extrude the outer rings of two load bearings respectively, with to the outer ring
Apply axial load；Load bearings cover for seat is located at the outer ring of two load bearings.
According to an embodiment of the present invention, the axle that the experiment axle coordinates provided with one with the inner ring of load bearings
Shoulder, two load bearings, which are located between the same side of the shaft shoulder, the inner ring of two load bearings, is provided with cone spacer,
A nut for being used to lock the inner ring is additionally provided with the experiment axle.
According to an embodiment of the present invention, the loading axis bearing and the second spacer ring are provided with oil leak hole.
According to an embodiment of the present invention, the two ends of the loading axis bearing are respectively equipped with and two load bearings
Outer ring coordinate shoulder block and back-up ring.
According to an embodiment of the present invention, the thickness of first spacer ring is less than the thickness of the second spacer ring.
According to an embodiment of the present invention, the gap between first spacer ring and the second spacer ring is 1~2mm.
According to an embodiment of the present invention, the load bearings and the bearing that the test bearing is same model.
According to an embodiment of the present invention, blind hole circumference uniform distribution on the end face of the second spacer ring.
As shown from the above technical solution, advantages and positive effects of the present invention are：
Aero-engine high-speed bearing of the present invention tests radial loading device, and load bearings are applied by the elastic force of spring
Axial load, it is ensured that load bearings normal work.Load bearings can select rotating speed, the suitable goods shelf productses of load, work
Make process stabilization reliable, do not result in the problem of roller departs from.If the test speed of test bearing is too high or load is excessive,
When choosing is less than suitable goods shelf productses, can from bearing with the same model of test bearing, therefore load bearings selection compared with
To be easy.
Brief description of the drawings
Its example embodiment is described in detail by referring to accompanying drawing, above and other feature of the invention and advantage will become
It is more obvious.
Fig. 1 is that the aero-engine high-speed bearing of an embodiment of the present invention tests the schematic diagram of radial loading device；
Fig. 2 is the schematic diagram of the second spacer ring in Fig. 1；
The right side that Fig. 3 is Fig. 2 regards schematic diagram；
Fig. 4 is the schematic diagram of the first spacer ring in Fig. 1；
Fig. 5 is the schematic diagram of the loading axis bearing in Fig. 1.
In figure：1st, axle is tested；2nd, test bearing；3rd, load bearings；4th, the first spacer ring；5th, the second spacer ring；6th, blind hole；7th, bullet
Spring；8th, loading axis bearing；9th, oil leak hole；10th, oil leak hole；11st, the shaft shoulder；12nd, nut；13rd, shoulder block；14th, back-up ring；15th, cone spacer.
Embodiment
Example embodiment is described more fully with referring now to accompanying drawing.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, thesing embodiments are provided so that the present invention will
Fully and completely, and by the design of example embodiment those skilled in the art is comprehensively conveyed to.Identical accompanying drawing in figure
Mark represents same or similar structure, thus will omit their detailed description.
Referring to Fig. 1 to Fig. 5, embodiment of the present invention discloses a kind of aero-engine high-speed bearing experiment radial loaded dress
Put, the high-speed bearing for being used to aero-engine carries out radial loaded load, to make to bearing by radial load
With lower and detected during high-speed rotation.When in use, a pair of complete high-speed bearings used are selected as to be tested
Test bearing.The loading device of the present invention includes experiment axle 1, two load bearings 3, the first spacer ring 4, the second spacer ring 5 and added
Carry bearing block 8.
Experiment axle 1 is horizontally disposed, is respectively used to connect a test bearing 2 at the two ends of experiment axle 1.Two load bearings
3 be the angular contact ball bearing of back-to-back configuration, and the inner ring of the two load bearings 3 is fixedly installed on the middle part of experiment axle 1, so that
Radial load can be more fifty-fifty applied on two test bearings 2.
As shown in Figure 1, in the present embodiment, the experiment axle 1 is used to coordinate with the inner ring of load bearings 3 provided with one
The shaft shoulder 11, the two load bearings 3 are located at the same side of the shaft shoulder 11, and are provided between the inner ring of two load bearings 3
Cone spacer 15, is additionally provided with a nut for being used to lock the inner ring of load bearings 3 on experiment axle 1.When in use, can be by two
The same side of individual load bearings 3 and cone spacer 15 from the shaft shoulder 11 is sequentially arranged on experiment axle 1.Cone spacer 15 is simple annulus
Structure, is coordinated between its endoporus and axle using small―gap suture, and external diameter is defined by the external diameter for being not more than load bearings inner ring, its width root
According to the first spacer ring 4 and the width design of the second spacer ring 5, it is ensured that between the first spacer ring 4 and the second spacer ring 5 after assembling have 1~
2mm gaps.
It will be apparent to a skilled person that the mode that two load bearings 3 are arranged on experiment axle 1 is not limited
System, as long as the inner ring of two load bearings 3 can be fixed on experiment axle 1.For example, it is also possible to which cone spacer 15 is set to
The shaft shoulder, two load bearings 3 are distributed in shaft shoulder both sides, and the outside of each load bearings 3 respectively sets a nut to be locked
Tightly.
Referring to Fig. 1 to Fig. 4, the first spacer ring 4 and the second spacer ring 5 are arranged between two load bearings 3.First spacer ring 4
It is circular part with the second spacer ring 5.The thickness of first spacer ring 4 can be less than the thickness of the second spacer ring 5, to reduce two
The space that spacer ring takes, the first spacer ring 4 can also be equal with the thickness of the second spacer ring 5.Between the first spacer ring 4 and the second spacer ring 5
There must be 1~2mm gap.
One is provided with being provided with the end face of the side of the first spacer ring 4 in multiple blind holes 6, each blind hole 6 for the second spacer ring 5
Individual spring 7, the spring 7 is contacted with the first spacer ring 4, and the elastic force that spring 7 is produced can promote the first spacer ring 4 and the second spacer ring
5 extrude the outer ring of the two load bearings 3 respectively, to apply axial load to the outer ring of two load bearings 3.The number of blind hole 6
The ratio for measuring the elastic force produced by the axial load of guarantee angular contact ball bearing normal work with single spring 7 is determined, is changed blind
The depth in hole 6 can adjust the elastic force of spring.The circumference on the end face of the second spacer ring of blind hole 6 is walked.
The actual loading value of spring of the present invention is that the minimum axial direction load according to needed for angular contact ball bearing normal work is true
It is fixed.In the blind hole 6 that designed spring 7 is put into the second spacer ring 5, coordinate the first spacer ring 4 to act on, produced by holddown spring 7
Elastic force, forms axial load, is applied to the outer ring of load bearings 3, stabilizes it work.Spring 7 is made of high-temperature alloy material,
Bearing part temperatures adjacent thereto are universal all very high during because of high-speed test (HST), often exceed 130 DEG C, and common spring steel is 130
During the work of DEG C temperatures above, it is likely that can be plastically deformed, cause spring failure, and then make to act on load bearings outer ring
Axial load skewness, causes load bearings deflection, has a strong impact on the normal work of bearing, and high temperature alloy spring then can be effective
Solve these problems.The spring profile size that the present invention is selected is tried one's best unanimously, and detector for outer diameter error is no more than ± 0.15mm, error in length
No more than ± 0.3mm, of substantially equal elastic force, load bearings outer ring energy could be so produced when spring is by compression equal length
By equidirectional uniform load.
Referring to Fig. 1 and Fig. 5, loading axis bearing 8 is set on the outer ring of two load bearings 3, that is to say, that two loadings
The outer ring of bearing 3 is nested in loading axis bearing, and the loading axis bearing 8 can be used for connecting hydraulic jack, hydraulic jack work
The Shi Huixiang loading axis bearings 8 apply radial load.Corresponding oil leak hole 9 is set in loading axis bearing 8, in the second spacer ring 5
On corresponding oil leak hole 10 can be set, oil leak hole 9 and 10 can make outflow of lubrication oil loading axis bearing 8 and the second spacer ring 5,
Avoid long-pending oil.Shoulder block 13 and gear that the outer ring of two load bearings 3 coordinates can be respectively arranged at the two ends of loading axis bearing 8
Circle 14, to prevent load bearings seat 8 from being automatically disengaged from load bearings 3.Loading axis bearing 8 uses the steel material system of some strength
Make, coordinate between the inwall of loading axis bearing 8 and the outer ring of load bearings 3 for gap, it is ensured that bearing outer ring can be in loading axis
Moved in bearing 8.
The load bearings 8 of the present invention can select rotating speed, the suitable goods shelf productses of load, and the course of work is reliable and stable, no
It can cause the problem of roller departs from.If the test speed of test bearing 2 is too high or load is excessive, select less than suitable shelf
During product, the bearing with the same model of test bearing 2 can be selected, therefore the selection of load bearings 3 is relatively easy to.In assembling
When, a load bearings 3 and cone spacer 15 are sequentially arranged on experiment axle 1 first, then erected experiment axle 1, axle
Taper end down, by the second spacer ring 5 load experiment axle 1 on, the blind hole on the second spacer ring 5 is put into blind hole upward, then by spring 7
In, and the first spacer ring 4 is placed on spring 7.Next the first spacer ring 4 and the second spacer ring 5 are comforted with hand, another is loaded
Bearing 3 is enclosed on experiment axle 1 and the inner ring of load bearings 3 is locked with nut 12, and loading axis bearing 8 finally is placed on into suitable frock
On, there is shoulder block side to place down, the shaft assembly assembled is installed in loading axis bearing by Action of Gravity Field from top to bottom, axle
The direction of component for axle taper end upward, finally back-up ring 14 is put into loading axis bearing neck again.
The illustrative embodiments of the present invention are particularly shown and described above.It should be understood that the invention is not restricted to institute
Disclosed embodiment, on the contrary, it is intended to cover comprising various modifications in the spirit and scope of the appended claims
And equivalent arrangements.
Claims (8)
1. a kind of aero-engine high-speed bearing tests radial loading device, it is characterised in that including：
Axle is tested, two ends are respectively used to connect a test bearing；
Two load bearings, two load bearings are the angular contact ball bearing of back-to-back configuration, and two loading axis
The inner ring held is fixedly installed on the middle part of the experiment axle；
First spacer ring and the second spacer ring, are arranged between two load bearings, close first spacer ring of second spacer ring
The end face of side, which is provided with multiple blind holes, the blind hole, is provided with spring；The spring contacts with the first spacer ring and promotes described
First spacer ring and the second spacer ring extrude the outer ring of two load bearings respectively, to apply axial load to the outer ring；
Loading axis bearing, is sheathed on the outer ring of two load bearings.
2. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that the examination
The shaft shoulder that axle coordinates provided with one with the inner ring of load bearings is tested, two load bearings are located at the same of the shaft shoulder
It is provided between side, the inner ring of two load bearings on cone spacer, the experiment axle and is additionally provided with one for locking in described
The nut of circle.
3. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described to add
Carry bearing block and the second spacer ring is provided with oil leak hole.
4. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described to add
The two ends for carrying bearing block are respectively equipped with the shoulder block and back-up ring coordinated with the outer ring of two load bearings.
5. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described the
The thickness of one spacer ring is less than the thickness of the second spacer ring.
6. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described the
Gap between one spacer ring and the second spacer ring is 1~2mm.
7. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described to add
Carry bearing and bearing of the test bearing for same model.
8. aero-engine high-speed bearing according to claim 1 tests radial loading device, it is characterised in that described blind
Hole circumference uniform distribution on the end face of the second spacer ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710408739.XA CN106989925A (en) | 2017-06-02 | 2017-06-02 | Aero-engine high-speed bearing tests radial loading device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710408739.XA CN106989925A (en) | 2017-06-02 | 2017-06-02 | Aero-engine high-speed bearing tests radial loading device |
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| CN106989925A true CN106989925A (en) | 2017-07-28 |
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| CN201710408739.XA Pending CN106989925A (en) | 2017-06-02 | 2017-06-02 | Aero-engine high-speed bearing tests radial loading device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108266458A (en) * | 2017-12-12 | 2018-07-10 | 北京卫星制造厂 | A kind of width temperature range angular contact shafting |
| CN109117509A (en) * | 2018-07-16 | 2019-01-01 | 中国航发沈阳发动机研究所 | The design method of aero-engine booster cavity |
| CN109580225A (en) * | 2019-01-09 | 2019-04-05 | 哈尔滨理工大学 | A kind of bearing test-bed radial loading device |
| US10882612B2 (en) * | 2018-07-30 | 2021-01-05 | Textron Innovations Inc. | Mast bearing system for a tiltrotor aircraft |
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| CN101975659A (en) * | 2010-08-27 | 2011-02-16 | 洛阳轴研科技股份有限公司 | High-speed dynamic simulation test method for electric mainshaft bearing |
| CN204359529U (en) * | 2014-12-15 | 2015-05-27 | 中国燃气涡轮研究院 | A kind of power load charger for aircraft bearing exerciser |
| CN105973604A (en) * | 2016-07-01 | 2016-09-28 | 宁波慈兴精密传动科技有限公司 | Electric automobile driving motor bearing high temperature high speed high load endurance testing apparatus |
| CN106706319A (en) * | 2016-12-26 | 2017-05-24 | 河南科技大学 | Cylinder roller bearing birotor testing machine shafting structure |
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2017
- 2017-06-02 CN CN201710408739.XA patent/CN106989925A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101975659A (en) * | 2010-08-27 | 2011-02-16 | 洛阳轴研科技股份有限公司 | High-speed dynamic simulation test method for electric mainshaft bearing |
| CN204359529U (en) * | 2014-12-15 | 2015-05-27 | 中国燃气涡轮研究院 | A kind of power load charger for aircraft bearing exerciser |
| CN105973604A (en) * | 2016-07-01 | 2016-09-28 | 宁波慈兴精密传动科技有限公司 | Electric automobile driving motor bearing high temperature high speed high load endurance testing apparatus |
| CN106706319A (en) * | 2016-12-26 | 2017-05-24 | 河南科技大学 | Cylinder roller bearing birotor testing machine shafting structure |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108266458A (en) * | 2017-12-12 | 2018-07-10 | 北京卫星制造厂 | A kind of width temperature range angular contact shafting |
| CN109117509A (en) * | 2018-07-16 | 2019-01-01 | 中国航发沈阳发动机研究所 | The design method of aero-engine booster cavity |
| CN109117509B (en) * | 2018-07-16 | 2023-06-23 | 中国航发沈阳发动机研究所 | Design method of aeroengine booster cavity |
| US10882612B2 (en) * | 2018-07-30 | 2021-01-05 | Textron Innovations Inc. | Mast bearing system for a tiltrotor aircraft |
| CN109580225A (en) * | 2019-01-09 | 2019-04-05 | 哈尔滨理工大学 | A kind of bearing test-bed radial loading device |
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Application publication date: 20170728 |