CN104062104B - Aero-engine compressor blade fatigue circulation test device - Google Patents
Aero-engine compressor blade fatigue circulation test device Download PDFInfo
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- CN104062104B CN104062104B CN201310105402.3A CN201310105402A CN104062104B CN 104062104 B CN104062104 B CN 104062104B CN 201310105402 A CN201310105402 A CN 201310105402A CN 104062104 B CN104062104 B CN 104062104B
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- compressor blade
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Abstract
The present invention relates to a kind of aero-engine compressor blade fatigue circulation test device, including centrifugal force charging assembly, the centrifugal force cyclic loading born during for simulating aero-engine compressor blade working, this assay device also includes dither charging assembly, the high frequency load born in time simulating aero-engine compressor blade working；Described dither charging assembly includes vibration table, the support A and the support B of fixing centrifugal force charging assembly of fixing compressor blade testpieces, and wherein, vibration table is for applying dither to compressor blade testpieces.Present configuration is simple and convenient to operate, the low cyclic loading of centrifugal force born when can simulate compressor blade work and high frequency load, make trystate completely the same with actual working state, realize centrifugal force load test and the high frequency load test of compressor blade, provide safe and reliable predetermined safe cycle life, it is to avoid use potential safety hazard.
Description
Technical field
The present invention relates to aerogenerator test field, specifically, relate to a kind of for testing aero-engine compressor blade
The assay device of performance.
Background technology
Compressor blade is as one of the key of aero-engine and vitals, for the structural intergrity of electromotor with use can
Having vital effect by property, the inefficacy of usual compressor blade will cause serious accident, even fatal crass.
So, for ensureing the use safety of compressor blade, it is necessary to provided the predetermined safe cycle life at its examination position by experiment.
But load suffered by compressor blade is more complicated, the low cyclic loading of centrifugal force to be born when electromotor real work,
But also dither load can be born.Under the experiment condition of existing assay device, it is only capable of simulation provides the low cyclic loading of centrifugal force,
High frequency load cannot be simulated so that trystate is inconsistent with actual working state, cause testing the pre-safety circulation longevity provided
Life credibility is the highest, there is use potential safety hazard.
Summary of the invention
Present invention aims to the problems referred to above that existing aero-engine compressor blade fatigue circulation test device exists,
Providing a kind of aero-engine compressor blade fatigue circulation test device, this assay device may be used for simulating compressor blade
The low cyclic loading of centrifugal force born during work and high frequency load, the pre-Dingan County be given for the existing assay device of solution and test method
Complete alternation life-span credibility is the highest, there is the problem offer research technique using potential safety hazard.
The technical scheme is that a kind of aero-engine compressor blade fatigue circulation test device, load including centrifugal force
Assembly, the centrifugal force cyclic loading born in time simulating aero-engine compressor blade working, this assay device also includes
Dither charging assembly, the high frequency load born in time simulating aero-engine compressor blade working；Described high frequency vibrating
Dynamic charging assembly includes vibration table, the support A and the support B of fixing centrifugal force charging assembly of fixing compressor blade testpieces,
Wherein, vibration table is for applying dither to compressor blade testpieces.
Preferably, compressor blade testpieces is fixed on the top of support A by blade fixed base, and the bottom of support A is fixed
On connecting plate C.
Preferably, centrifugal force charging assembly is positioned at the side of compressor blade testpieces, the opposite side of compressor blade testpieces
It is provided with gimbal lever's assembly.
Preferably, one end of gimbal lever's assembly is fixed on blade fixed base, and the other end is fixed on connecting plate B.
Preferably, centrifugal force charging assembly is fixed on the top of support B, and the bottom of support B is fixed on connecting plate D.
Preferably, centrifugal force charging assembly includes connecting plate A, load bar, pressurized strut, sensor and load bar bearing, adds
The one end carrying bar is connected with sensor side by pressurized strut, and the other end is fixed on connecting plate A, and the opposite side of sensor passes through
Fixing bar is connected with the briquetting being arranged in compressor blade testpieces pin-and-hole, and fixing bar is sleeved in load bar bearing, load bar
Bearing is positioned at the top of support B.
Preferably, fixing bar one end connects sensor, and the other end is connected with briquetting by load plate.
Preferably, load plate is connected with briquetting by steel wire rope, and the outer cover of steel wire rope is equipped with the collar.
The invention have the benefit that present configuration is simple and convenient to operate, under test conditions, by the centrifugal force arranged
Charging assembly and dither charging assembly, it is possible to the low cyclic loading of centrifugal force born during simulation compressor blade work and high frequency
Load so that trystate is completely the same with actual working state, it is achieved the centrifugal force load test of compressor blade and high frequency carry
Lotus is tested, provide safe and reliable predetermined safe cycle life, it is to avoid use potential safety hazard, solve existing test method to
The predetermined safe cycle life credibility gone out is the highest, there is the problem using potential safety hazard.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
Fig. 2 is the top view of the present invention.
Detailed description of the invention
The invention will be further described below in conjunction with the accompanying drawings.
A kind of aero-engine compressor blade fatigue circulation test device that the present invention provides, including centrifugal force charging assembly, uses
The centrifugal force cyclic loading born in time simulating aero-engine compressor blade working, this assay device also includes dither
Charging assembly, the high frequency load born in time simulating aero-engine compressor blade working；Described dither loading group
Part includes vibration table 15, the support A13 and the support B16 of fixing centrifugal force charging assembly of fixing compressor blade testpieces 8,
Wherein, vibration table 15 is for applying dither to compressor blade testpieces 8.
For the ease of compressor blade testpieces 8 applies corresponding load, compressor blade testpieces 8 passes through blade fixed base
10 tops being fixed on support A13, the bottom of support A is fixed on connecting plate C.
Centrifugal force charging assembly is positioned at the side of compressor blade testpieces 8, tests compressor blade at centrifugal force charging assembly
When part 8 applies centrifugal force low cyclic loading, in order to prevent compressor blade testpieces 8 single load bearing and support A13 from being forgotten about it,
The opposite side of compressor blade testpieces 8 is provided with gimbal lever's assembly 11, loads, for balancing, the moment that centrifugal force produces.
Loading, in order to balance, the moment that centrifugal force produces, one end of above-mentioned gimbal lever assembly 11 is fixed on blade fixed base 10,
The other end is fixed on connecting plate B12.
Centrifugal force charging assembly is fixed on the top of support B16, and the bottom of support B16 is fixed on connecting plate D17.
Centrifugal force charging assembly includes connecting plate A1, load bar 2, pressurized strut 3, sensor 4 and load bar bearing 5, loads
One end of bar 2 is connected with sensor 4 side by pressurized strut 3, and the other end is fixed on connecting plate A1, sensor 4 another
Side is connected with the briquetting 9 being arranged in compressor blade testpieces 8 pin-and-hole by fixing bar, and fixing bar is sleeved on load bar and props up
In seat 5, load bar bearing 5 is positioned at the top of support B16, and load bar bearing is used for supporting connecting plate A1, load bar 2, making
Dynamic cylinder 3 and sensor 4, and ensure that the direction of power that pressurized strut applies is perpendicular to forcing press leaf assay part 8 pin-and-hole axis.
In order to realize the connection between sensor 4 and briquetting 9, above-mentioned fixing bar one end connects sensor 4, and the other end is by adding
Support plate 18 is connected with briquetting 9.
In order to ensure direction and the size that centrifugal force loads, above-mentioned load plate 18 is connected with briquetting 9 by two steel wire ropes 6, for
Being further ensured that the direction that centrifugal force loads, the outer cover of above-mentioned steel wire rope 6 is equipped with the collar 7.
Operation principle: when simulation provides centrifugal force low cyclic loading, pressurized strut 3 action, compressor blade when working for electromotor
Testpieces 8 provides centrifugal force, and simulates low cyclic loading, and sensor 4 is measured and monitors the change of centrifugal force, is being centrifuged
When power loads, ensure the correct of centrifugal force loading direction and size by steel wire rope 6, simultaneously by the collar 7 by two steel wire ropes
6 are close together, and are further ensured that centrifugal force loading direction is correct；The moment loading centrifugal force generation is entered by gimbal lever's assembly simultaneously
Row balance, prevents compressor blade testpieces 8 single load bearing and support A from being forgotten about it.
When simulation provides high frequency load, vibration table 15 applies dither to compressor blade testpieces 8.
Claims (7)
1. an aero-engine compressor blade fatigue circulation test device, including centrifugal force charging assembly, is used for simulating aeroplane engine
The centrifugal force cyclic loading born during the work of machine compressor blade, it is characterised in that: this assay device also includes dither
Charging assembly, the high frequency load born in time simulating aero-engine compressor blade working；Described dither loads
Assembly includes vibration table (15), the support A (13) of fixing compressor blade testpieces (8) and fixing centrifugal force loading group
The support B (16) of part, wherein, vibration table (15) is for applying dither to compressor blade testpieces；Centrifugal force adds
Carry assembly and include connecting plate A (1), load bar (2), pressurized strut (3), sensor (4) and load bar bearing (5), add
The one end carrying bar (2) is connected with sensor (4) side by pressurized strut (3), and the other end is fixed on connecting plate A (1)
On, the opposite side of sensor (4) is by fixing bar and the briquetting (9) being arranged in compressor blade testpieces (8) pin-and-hole
Connecting, fixing bar is sleeved in load bar bearing (5), and load bar bearing (5) is positioned at the top of support B (16).
Aero-engine compressor blade fatigue circulation test device the most according to claim 1, it is characterised in that: gas compressor blade
Sheet testpieces (8) is fixed on the top of support A (13) by blade fixed base (10), and the bottom of support A (13) is solid
It is scheduled on connecting plate C (14).
Aero-engine compressor blade fatigue circulation test device the most according to claim 1, it is characterised in that: centrifugal force adds
Carrying assembly and be positioned at the side of compressor blade testpieces (8), the opposite side of compressor blade testpieces (8) is provided with balance
Bar assembly (11).
Aero-engine compressor blade fatigue circulation test device the most according to claim 3, it is characterised in that: gimbal lever's group
One end of part (11) is fixed on blade fixed base (10), and the other end is fixed on connecting plate B (12).
Aero-engine compressor blade fatigue circulation test device the most according to claim 1, it is characterised in that: centrifugal force adds
Carrying assembly and be fixed on the top of support B (16), the bottom of support B (16) is fixed on connecting plate D (17).
Aero-engine compressor blade fatigue circulation test device the most according to claim 1, it is characterised in that: fixing bar one
End connects sensor (4), and the other end is connected with briquetting (9) by load plate (18).
Aero-engine compressor blade fatigue circulation test device the most according to claim 6, it is characterised in that: load plate (18)
Being connected with briquetting (9) by steel wire rope (6), the outer cover of steel wire rope (6) is equipped with the collar (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310105402.3A CN104062104B (en) | 2013-03-19 | 2013-03-19 | Aero-engine compressor blade fatigue circulation test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310105402.3A CN104062104B (en) | 2013-03-19 | 2013-03-19 | Aero-engine compressor blade fatigue circulation test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104062104A CN104062104A (en) | 2014-09-24 |
| CN104062104B true CN104062104B (en) | 2016-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310105402.3A Expired - Fee Related CN104062104B (en) | 2013-03-19 | 2013-03-19 | Aero-engine compressor blade fatigue circulation test device |
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| CN107957326A (en) * | 2016-10-17 | 2018-04-24 | 中国人民解放军装甲兵工程学院 | A kind of testing machine |
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| CN107860565A (en) * | 2017-10-11 | 2018-03-30 | 昌河飞机工业（集团）有限责任公司 | A kind of loading device of helicopter simulating blade stress |
| CN108036911B (en) * | 2017-12-13 | 2020-04-28 | 中国飞机强度研究所 | Test device for measuring damping vibration attenuation effect of turbine movable blade |
| CN108168894B (en) * | 2017-12-13 | 2020-03-06 | 中国飞机强度研究所 | Method for simulating centrifugal force of turbine moving blade |
| CN108931349B (en) * | 2018-04-09 | 2020-08-18 | 南京航空航天大学 | Centrifugal force simulation test device used in high-speed hard object impact test |
| CN108593472A (en) * | 2018-06-11 | 2018-09-28 | 中国航发哈尔滨东安发动机有限公司 | Auto-bank unit guide tube high-cycle fatigue test device |
| CN109238615B (en) * | 2018-11-05 | 2020-12-01 | 苏州东菱振动试验仪器有限公司 | Device and method for balancing centrifugal force and electromagnetic vibration table |
| CN109900461B (en) * | 2019-02-27 | 2020-12-01 | 东软医疗系统股份有限公司 | Method and device for testing safety of CT rotating plate |
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| CN111649926B (en) * | 2020-06-08 | 2022-05-17 | 中国航发北京航空材料研究院 | Axial and vibration high-low cycle composite fatigue test device |
| CN113405791A (en) * | 2021-07-01 | 2021-09-17 | 中国航发沈阳发动机研究所 | Fatigue test device for elastic support of aero-engine |
| CN116754208B (en) * | 2023-08-16 | 2023-11-07 | 天津航天瑞莱科技有限公司 | Fatigue test device for static blade adjusting mechanism assembly of compressor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3637284B2 (en) * | 2001-03-01 | 2005-04-13 | 三菱重工業株式会社 | Rotor blade frequency estimating apparatus and method |
| CN201397223Y (en) * | 2009-05-08 | 2010-02-03 | 中能风电设备有限公司 | Vibrator for blade testing |
| CN201408112Y (en) * | 2009-05-25 | 2010-02-17 | 上海同韵环保能源科技有限公司 | Loading test device for fan blade of wind generating set |
| CN201464169U (en) * | 2009-07-02 | 2010-05-12 | 天津鑫茂鑫风能源科技有限公司 | Excitation method experimental device for fatigue test of large-sized wind power vanes |
| CN102156035B (en) * | 2011-03-24 | 2012-09-05 | 西安交通大学 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
| CN102410916B (en) * | 2011-12-02 | 2014-02-26 | 东南大学 | Experimental apparatus and method for vibration characteristic of turbine moving blade |
| CN203203788U (en) * | 2013-03-19 | 2013-09-18 | 徐可君 | Fatigue cycle test apparatus for compressor blade of aeroengine |
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- 2013-03-19 CN CN201310105402.3A patent/CN104062104B/en not_active Expired - Fee Related
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| CN104062104A (en) | 2014-09-24 |
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Granted publication date: 20161228 Termination date: 20170319 |