CN205300883U - High all fatigue test devices of aeroengine centrifugation impeller blade and fixture device thereof - Google Patents
High all fatigue test devices of aeroengine centrifugation impeller blade and fixture device thereof Download PDFInfo
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- CN205300883U CN205300883U CN201620029880.XU CN201620029880U CN205300883U CN 205300883 U CN205300883 U CN 205300883U CN 201620029880 U CN201620029880 U CN 201620029880U CN 205300883 U CN205300883 U CN 205300883U
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 26
- 238000005119 centrifugation Methods 0.000 title abstract 2
- 230000003321 amplification Effects 0.000 claims description 21
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 21
- 230000014759 maintenance of location Effects 0.000 abstract 3
- 238000012360 testing method Methods 0.000 description 18
- 230000005284 excitation Effects 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002372 labelling Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000003556 assay Methods 0.000 description 1
- 238000012217 deletion Methods 0.000 description 1
- 230000037430 deletion Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
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Abstract
The utility model discloses a high all fatigue test devices of aeroengine centrifugation impeller blade and fixture device thereof, fixture device include blade retention device, bottom plate, enlarge roof beam and a pair of adjustment cushion, the lower mounting that is provided with the mounting on the bottom plate and is used for being fixed in the bottom plate shaking table, the position that corresponds with last mounting on the enlarged roof beam is provided with the bottom plate mounting, and the blade retention device is with testpieces blade retention in the upper surface that enlargies the roof beam, to enlarge the roof beam through bottom plate mounting and last mounting is fixed in the bottom plate, a pair of adjusting pad pad is located and is enlargied between roof beam and the bottom plate, and is located the both sides of testpieces blade respectively, is provided with waist shape through -hole on each adjusting pad, and a plurality of connecting pieces pass vertical length that ultimate range between same waist shape through -hole and each connecting piece is less than waist shape through -hole. The utility model discloses can make the blade satisfy fatigue failure's requirement in the shaking table thrust range.
Description
Technical field
This utility model relates to aero engine technology field, particularly relates to a kind of assay device for aero-engine centrifugal impeller individual blade high-cycle fatigue test and grip device thereof.
Background technology
Aero-engine centrifugal impellers blades is the key component of aero-engine, often bears alternate load. The vibration fatigue test of blade is used for the fatigue life determining blade under different alternate loads, or determines blade fatigue limit under guideline lives, it is possible to be used for carrying out accident analysis and Curve guide impeller inspection.
For a long time, aero-engine centrifugal impellers blades high-cycle fatigue test is all make centrifugal impellers blades cantilever fixing be installed on vibration table and carry out high-cycle fatigue test either directly through pressing plate. During test, under blade first-order flexure natural frequency, produce the vibration of big displacement amplitude, allow the most dangerouse cross-section place of blade produce big stress and fatigue rupture.
But, in prior art, during by a vibration table blade is carried out high stress level vibration fatigue test, when table top maximum thrust often occurs, vibratory response level on blade still cannot make blade fatigue rupture occur, causes the fatigue limit result of the test that finally can not get this model blade.
The above-mentioned test method of prior art, it is make centrifugal impellers blades cantilever fixing be installed on vibration table and carry out high-cycle fatigue test either directly through pressing plate, but due to the shape of aero-engine centrifugal impellers blades many as be that blade root width, blade are short, during test, blade is allowed to produce the vibration of big displacement amplitude extremely difficult, therefore, under vibration table maximum thrust, the vibration displacement of blade still cannot make blade produce fatigue rupture. It is easy to produce damage it addition, vibration table works for a long time under maximum thrust, full-load conditions.
Accordingly, it would be desirable to develop a kind of novel test device for aero-engine centrifugal impellers blades high-cycle fatigue test.
In information above-mentioned disclosed in described background section only for strengthening the understanding to background of the present utility model, therefore it can include not constituting the information to prior art known to persons of ordinary skill in the art.
Utility model content
A main purpose of the present utility model is in that to overcome at least one defect of above-mentioned prior art, a kind of grip device for aero-engine centrifugal impellers blades high-cycle fatigue test is provided, the excitation making vibration table is exaggerated when being transferred to blade, meets test requirements document and makes blade fatigue rupture occur.
Another main purpose of the present utility model is in that to overcome at least one defect of above-mentioned prior art, a kind of aero-engine centrifugal impellers blades high-cycle fatigue test device with this utility model grip device is provided, the excitation making vibration table is exaggerated when being transferred to blade, meets test requirements document and makes blade fatigue rupture occur.
For realizing above-mentioned utility model purpose, this utility model adopts the following technical scheme that
According to an aspect of the present utility model, it is provided that a kind of grip device:
A kind of grip device, for aero-engine centrifugal impellers blades high-cycle fatigue test, described grip device includes: blade is fixed device, base plate, amplification beam and adjusts cushion block a pair; Described base plate is provided with upper fixing element and for described base plate being fixed on the lower fixture of vibration table; On described amplification beam, the position corresponding with fixed part is provided with the base plate fixture for described amplification beam is fixed on described base plate, and testpieces blade is fixed on the upper surface of described amplification beam by the fixing device of described blade; By described base plate fixture and upper fixing element so that described amplification beam is fixed on described base plate; The pair of adjustment cushion block pad is located between described amplification beam and described base plate, and lay respectively at the both sides of described testpieces blade, each described adjustment cushion block is provided with waist through hole, multiple described connectors are through same described waist through hole, and the ultimate range between each described connector is less than the longitudinal length of described waist through hole.
Grip device of the present utility model, it is preferred that regulating the spacing of cushion block described in a pair is that the first-order flexure frequency so that described amplification beam is identical with the first-order flexure frequency of described testpieces blade or the spacing of difference 1%.
Grip device of the present utility model, it is preferred that be provided with length scale or the scale that has been sticked on described amplification beam.
Grip device of the present utility model, it is preferred that described connector is bolt.
Grip device of the present utility model, it is preferred that four corner correspondence positions that the fixing device of described blade includes top board and lower platen, described top board and described lower platen are provided with through hole.
Grip device of the present utility model, it is preferred that described lower fixture is bolt hole, fixed part is screwed hole.
Grip device of the present utility model, it is preferred that the upper surface of described amplification beam is provided with the screwed hole corresponding with the lead to the hole site of the through hole of described top board, described lower platen.
Grip device of the present utility model, it is preferred that the symmetrical both sides being arranged at described testpieces blade of the pair of adjustment cushion block.
Grip device of the present utility model, it is preferred that described base plate fixture is through hole.
According to another aspect of the present utility model, it is provided that a kind of aero-engine centrifugal impellers blades high-cycle fatigue test device with this utility model grip device.
As shown from the above technical solution, advantage of the present utility model and have the active effect that grip device of the present utility model so that the excitation of vibration table is exaggerated when being transferred to blade, and test requirements document can be met make blade that fatigue rupture to occur.
Grip device for aero-engine centrifugal impeller individual blade high-cycle fatigue test of the present utility model, by the resonance of girder construction, is exaggerated the vibratory response of blade, blade can be made to meet the requirement of fatigue rupture in vibration table thrust range.
Accompanying drawing explanation
Considering the following detailed description to preferred embodiment of the present utility model in conjunction with the drawings, various targets of the present utility model, feature and advantage will become apparent from. Accompanying drawing is only exemplary diagram of the present utility model, is not necessarily drawn to scale. In the accompanying drawings, same accompanying drawing labelling represents same or similar parts all the time.
Fig. 1 is the schematic top plan view of the grip device of this utility model embodiment.
Fig. 2 is the A-A sectional view in Fig. 1.
Fig. 3 is the schematic top plan view of the base plate of the grip device of this utility model embodiment.
Fig. 4 is the schematic top plan view regulating cushion block of the grip device of this utility model embodiment.
Fig. 5 is the B-B sectional view in Fig. 4.
Fig. 6 is the schematic top plan view amplifying beam of the grip device of this utility model embodiment.
Detailed description of the invention
It is described more fully with example embodiment referring now to accompanying drawing. But, example embodiment can be implemented in a variety of forms, and is not understood as limited to embodiment set forth herein; On the contrary, it is provided that these embodiments make this utility model will fully and completely, and the design of example embodiment is conveyed to those skilled in the art all sidedly. Accompanying drawing labelling identical in figure represents same or similar structure, thus will omit their detailed description.
When the element of this utility model or this utility model preferred embodiment is described, word " ", " one ", " being somebody's turn to do " and " described " are intended to refer to there is one or more element. Term " includes ", " comprising " and " having " etc. is intended to opening and refers to and also can there is other element except listed element.
The grip device of this utility model embodiment, can be used for but be not limited to the aero-engine centrifugal impellers blades high-cycle fatigue test device for this utility model embodiment. The aero-engine centrifugal impellers blades high-cycle fatigue test device of this utility model embodiment, has the grip device of this utility model embodiment.
As depicted in figs. 1 and 2, the grip device of this utility model embodiment includes base plate 1, right adjustment cushion block 2, amplifies beam 3, top board 5, lower platen 6 and left adjustment cushion block 7, top board 5 therein, lower platen 6, be the fixing device of the blade for fixation test part blade 4.
As shown in Figure 3, in the present embodiment, base plate 1 has 8 bolts hole (bolt hole 11, bolt hole 12, bolt hole 13, bolt hole 14, bolt hole 15, bolt hole 22, bolt hole 23, bolt hole 24), it is possible to be fixed on by base plate 1 by 8 bolts hole with bolt on the moveable top of vibration table of the aero-engine centrifugal impellers blades high-cycle fatigue test device of this utility model embodiment. Grip device of the present utility model, it is not limited to use bolt hole as lower fixture, be fixed by bolt and vibration table, it is possible to use other fixed form.
As shown in Figure 3, base plate 1 has 12 screwed holes (screwed hole 8, screwed hole 9, screwed hole 10, screwed hole 16, screwed hole 17, screwed hole 18, screwed hole 19, screwed hole 20, screwed hole 21, screwed hole 25, screwed hole 26, screwed hole 27), as shown in Figure 4 and Figure 5, right adjustment cushion block 2, left adjustment cushion block 7 all have two waist through hole (or claiming elongated hole) 28, the effect of waist through hole 28, it is that the bolt for connection amplification beam 3 with base 1 passes, with when adjusting the first-order flexure frequency amplifying beam 3, it is possible to bolt need not be removed and be made directly adjustment.Such as, through through hole 29, through hole 30, through hole 31, it is threaded into three bolts of hole 8, screwed hole 9, screwed hole 10 respectively, through same waist through hole 28, the longitudinal length of waist through hole 28 is then more than the spacing of screwed hole 8 and screwed hole 10, can conveniently carry out the adjustment of spacing between right adjustment cushion block 2 and left adjustment cushion block 7, bolt need not be removed, add test efficiency.
Grip device of the present utility model, it is not limited to use bolt hole as upper fixing element, is fixed with amplifying beam 3. And the connector connecting amplification beam 3 and base plate 1 is also not limited to be bolt.
As shown in Figure 6, amplify and beam 3 has 12 through holes (through hole 29, through hole 30, through hole 31, through hole 34, through hole 35, through hole 36, through hole 37, through hole 38, through hole 39, through hole 42, through hole 43, through hole 44), as shown in Figure 6, by amplifying the waist through hole 28 on 12 through holes on beam 3, right adjustment cushion block 2 and left adjustment cushion block 7 and 6 screwed holes on base plate 1, amplification beam 3, right adjustment cushion block 2, left adjustment cushion block 7 and base plate 1 are connected with bolt, form girder construction. Grip device of the present utility model, it is not limited to use through hole as base plate fixture, be fixed with base plate 1.
As shown in Figure 6, amplify and beam 3 has 4 screwed holes (screwed hole 32, screwed hole 33, screwed hole 40, screwed hole 41), by amplifying the screwed hole on beam 3, testpieces blade 4, top board 5 and lower platen 6 are fixed on the upper surface amplifying beam 3 with bolt.
When testing, need to first debug, frequency test equipment can be passed through, for instance signal generator etc., obtain the first-order flexure frequency f of testpieces blade 41And amplify the first-order flexure frequency f of beam 32, wherein, right adjustment cushion block 2 and have waist through hole 28 on left adjustment cushion block 7, by regulating the distance between right adjustment cushion block 2 and left adjustment cushion block 7, change the first-order flexure frequency f amplifying beam 32, until amplifying the first-order flexure frequency f of beam 32With testpieces blade 4 first-order flexure frequency f1Identical or difference 1%, namelyThe debugging of grip device frequency terminates. First-order flexure frequency is also referred to as first-order modal corner frequency.
Above-mentioned adjustment carries out after fixing each bolt. Owing to being regulate cushion block 2,7 along vertically moving of waist through hole 28, therefore eliminate the operation of assembling-disassembling bolt, add test efficiency. Frequency adjust after regulate cushion block 2,7 end not necessarily with amplify beam 3 end part aligning, but regulate cushion block 2, the 7 preferably symmetrical both sides being arranged at testpieces blade 4. Length scale or the scale that is sticked can be set on amplification beam 3, in order to improve the efficiency that frequency adjusts.
And regulate the length of cushion block 2,7 above-below direction in FIG more than or equal to amplifying the beam 3 length in the direction, to ensure the effective support amplifying beam 3.
During test, carrying out under the resonant frequency of the first-order flexure frequency of testpieces blade 4, the excitation load of vibration table is transferred in testpieces blade 4 process, owing to amplifying the first-order flexure frequency f of beam 32First-order modal corner frequency f with testpieces blade 41Essentially coincide, now amplify beam 3 to resonate simultaneously, then the vibratory response on testpieces blade 4 is exaggerated, and can more easily make testpieces blade 4 that fatigue rupture occurs, by analyzing certain model aero-engine centrifugal impeller individual blade high-cycle fatigue test data, when testing under 60% excitation of vibration table maximum thrust, the vibratory response on testpieces blade 4 is exaggerated 10 times and produces fatigue rupture.
Aero-engine centrifugal impellers blades high-cycle fatigue test device of the present utility model, the test principle carrying out aero-engine centrifugal impeller individual blade high-cycle fatigue test is to make test block blade 4 large-amplitude vibration under first-order flexure resonant frequency under cantilever fixing state, allows the most dangerouse cross-section place of test block blade 4 produce high stress fatigue brisement. Exciting force is provided by the electric vibration table of aero-engine centrifugal impellers blades high-cycle fatigue test device of the present utility model, the quality of moveable top and grip device is much larger than the quality of testpieces blade 4, with the electro-magnetic exciting force exciting moveable top of Frequency Adjustable, when the frequency of exciting force is substantially equal to the natural frequency of vibration of testpieces blade 4, moveable top is substantially stationary with grip device, and testpieces blade 4 can carry out permanent width vibration under required amplitude. Adjust the size of power amplifier output energy of aero-engine centrifugal impellers blades high-cycle fatigue test device of the present utility model to regulate the amplitude of testpieces blade 4 so that it is remain stable for, until only producing fatigue crack.
Therefore by the grip device of this utility model embodiment, it is possible to allow vibration table not carry out just allowing in full-load test situation the blade enough vibratory responses of acquisition so that blade generation fatigue rupture under maximum thrust.
Should be understood that multiple example described above can along multiple directions (as tilted, reverse, level, vertical, etc.) and be utilized with multiple structures, without departing from principle of the present utility model. Embodiment shown in accompanying drawing is only used as the example of the effectively application of principle of the present utility model and is shown and described, and this utility model is not limited to any concrete details of these embodiments.
Certainly, once think over the above description of representative embodiment, those skilled in the art just will readily appreciate that, these specific embodiments can be made multiple remodeling, interpolation, replacement, deletion and other changes, and these changes are in the scope of principle of the present utility model. Therefore, detailed description above should be clearly understood that it is that spirit and scope of the present utility model only limit by appended claims and equivalent thereof only to illustrate and to provide in the way of example.
Claims (10)
1. a grip device, for aero-engine centrifugal impellers blades high-cycle fatigue test, it is characterised in that described grip device includes:
Blade fixes device;
Base plate, described base plate is provided with upper fixing element and for described base plate is fixed on the lower fixture of vibration table;
Amplifying beam, on described amplification beam, the position corresponding with fixed part is provided with the base plate fixture for described amplification beam is fixed on described base plate, and testpieces blade is fixed on the upper surface of described amplification beam by the fixing device of described blade;
Connector, by described base plate fixture and upper fixing element so that described amplification beam is fixed on described base plate; And
Regulate cushion block a pair, pad is located between described amplification beam and described base plate, and lay respectively at the both sides of described testpieces blade, each described adjustment cushion block is provided with waist through hole, multiple described connectors are through same described waist through hole, and the ultimate range between each described connector is less than the longitudinal length of described waist through hole.
2. grip device as claimed in claim 1, it is characterised in that regulate described in a pair the spacing of cushion block be the first-order flexure frequency so that described amplification beam identical with the first-order flexure frequency of described testpieces blade or differ 1% spacing.
3. grip device as claimed in claim 2, it is characterised in that be provided with length scale or the scale that has been sticked on described amplification beam.
4. grip device as claimed in claim 1, it is characterised in that described connector is bolt.
5. grip device as claimed in claim 3, it is characterised in that four corner correspondence positions that the fixing device of described blade includes top board and lower platen, described top board and described lower platen are provided with through hole.
6. grip device as claimed in claim 1, it is characterised in that described lower fixture is bolt hole, and fixed part is screwed hole.
7. grip device as claimed in claim 5, it is characterised in that the upper surface of described amplification beam is provided with the screwed hole corresponding with the lead to the hole site of the through hole of described top board, described lower platen.
8. grip device as claimed in claim 1, it is characterised in that the symmetrical both sides being arranged at described testpieces blade of the pair of adjustment cushion block.
9. grip device as claimed in claim 1, it is characterised in that described base plate fixture is through hole.
10. an aero-engine centrifugal impellers blades high-cycle fatigue test device, it is characterised in that described aero-engine centrifugal impellers blades high-cycle fatigue test device has the arbitrary described grip device of claim 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620029880.XU CN205300883U (en) | 2016-01-13 | 2016-01-13 | High all fatigue test devices of aeroengine centrifugation impeller blade and fixture device thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620029880.XU CN205300883U (en) | 2016-01-13 | 2016-01-13 | High all fatigue test devices of aeroengine centrifugation impeller blade and fixture device thereof |
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| CN205300883U true CN205300883U (en) | 2016-06-08 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248331A (en) * | 2016-08-30 | 2016-12-21 | 中国人民解放军空军工程大学航空航天工程学院 | Vibration amplifier and the test method of simulation blade high-order nonlinear vibrating fatigue |
| CN107421984A (en) * | 2017-08-31 | 2017-12-01 | 北京航空航天大学 | A kind of hollow turbine vane is superimposed high Zhou Zhendong thermal mechanical fatigue pilot system and method |
| CN108254144A (en) * | 2017-12-25 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of Split vane frequency reducing structure measured for the high cycle fatigue limit |
| CN108393818A (en) * | 2018-01-16 | 2018-08-14 | 中国航发贵州黎阳航空动力有限公司 | A kind of compressor arc tooth vibration of rotor blades fatigue test clamper |
| CN108918070A (en) * | 2018-08-28 | 2018-11-30 | 苏州长菱测试技术有限公司 | A kind of vibration fatigue test device for high frequency stress blade |
| CN109163870A (en) * | 2018-09-13 | 2019-01-08 | 苏州长菱测试技术有限公司 | The method amplified girder construction and improve Amplitude Ration in vibration fatigue test of blade |
| CN112763172A (en) * | 2020-12-29 | 2021-05-07 | 上海发电设备成套设计研究院有限责任公司 | Amplification device for acceleration of earthquake test bed |
| CN112781812A (en) * | 2019-11-01 | 2021-05-11 | 上海羿弓氢能科技有限公司 | Fatigue testing method for metal diaphragm of diaphragm compressor |
| CN113884260A (en) * | 2020-07-01 | 2022-01-04 | 中国航发商用航空发动机有限责任公司 | Vibration level amplification vibration fatigue test fixture |
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2016
- 2016-01-13 CN CN201620029880.XU patent/CN205300883U/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248331A (en) * | 2016-08-30 | 2016-12-21 | 中国人民解放军空军工程大学航空航天工程学院 | Vibration amplifier and the test method of simulation blade high-order nonlinear vibrating fatigue |
| CN107421984A (en) * | 2017-08-31 | 2017-12-01 | 北京航空航天大学 | A kind of hollow turbine vane is superimposed high Zhou Zhendong thermal mechanical fatigue pilot system and method |
| CN107421984B (en) * | 2017-08-31 | 2018-11-16 | 北京航空航天大学 | A kind of hollow turbine vane is superimposed the thermal mechanical fatigue pilot system and method for high Zhou Zhendong |
| CN108254144A (en) * | 2017-12-25 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of Split vane frequency reducing structure measured for the high cycle fatigue limit |
| CN108393818A (en) * | 2018-01-16 | 2018-08-14 | 中国航发贵州黎阳航空动力有限公司 | A kind of compressor arc tooth vibration of rotor blades fatigue test clamper |
| CN108918070A (en) * | 2018-08-28 | 2018-11-30 | 苏州长菱测试技术有限公司 | A kind of vibration fatigue test device for high frequency stress blade |
| CN109163870A (en) * | 2018-09-13 | 2019-01-08 | 苏州长菱测试技术有限公司 | The method amplified girder construction and improve Amplitude Ration in vibration fatigue test of blade |
| CN112781812A (en) * | 2019-11-01 | 2021-05-11 | 上海羿弓氢能科技有限公司 | Fatigue testing method for metal diaphragm of diaphragm compressor |
| CN113884260A (en) * | 2020-07-01 | 2022-01-04 | 中国航发商用航空发动机有限责任公司 | Vibration level amplification vibration fatigue test fixture |
| CN113884260B (en) * | 2020-07-01 | 2024-04-19 | 中国航发商用航空发动机有限责任公司 | Vibration level amplifying vibration fatigue test fixture |
| CN112763172A (en) * | 2020-12-29 | 2021-05-07 | 上海发电设备成套设计研究院有限责任公司 | Amplification device for acceleration of earthquake test bed |
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Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |