CN104062104A - Cyclic test device for fatigue of aeroengine compressor blade - Google Patents
Cyclic test device for fatigue of aeroengine compressor blade Download PDFInfo
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- CN104062104A CN104062104A CN201310105402.3A CN201310105402A CN104062104A CN 104062104 A CN104062104 A CN 104062104A CN 201310105402 A CN201310105402 A CN 201310105402A CN 104062104 A CN104062104 A CN 104062104A
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Abstract
The invention relates to a cyclic test device for fatigue of an aeroengine compressor blade. The cyclic test device comprises a centrifugal force loading assembly for simulating cyclic loading of centrifugal force on the aeroengine compressor blade during working; the test device also comprises a high-frequency vibration loading assembly for simulating high-frequency loads on the aeroengine compressor blade during working; the high-frequency vibration loading assembly comprises vibrating table, a support A for fixing a compressor blade test piece and a support B for fixing the centrifugal force loading assembly, wherein the vibrating table is used for applying high-frequency vibration on the compressor blade test piece. The cyclic test device for the fatigue of the aeroengine compressor blade is simple in structure and convenient to operate; the cyclic test device is capable of simulating the low cyclic loading of the centrifugal force and the high-frequency loads on the aeroengine compressor blade during working so that the test state is completely consistent with the actual working state, and therefore, the centrifugal force loading test and the high-frequency load test of the compressor blade are realized, completely trustable predetermined safe cycle life is provided and then potential safety hazards in use can be avoided.
Description
Technical field
The present invention relates to aerogenerator test field, specifically, relate to a kind of for testing the test unit of aero-engine compressor Blade Properties.
Background technology
Compressor blade is as one of the key of aeromotor and vitals, for structural intergrity and the dependability of engine, has vital effect, and the inefficacy of compressor blade will cause serious accident, even fatal crass conventionally.So, for guaranteeing the use safety of compressor blade, must provide by experiment the predetermined safe cycle life at its examination position.But due to the suffered load more complicated of compressor blade, when engine real work, not only to bear the low cyclic loading of centrifugal force, but also can bear dither load.Under the experiment condition of existing test unit, only can simulate and provide the low cyclic loading of centrifugal force, cannot simulate high frequency load, make trystate and actual working state inconsistent, the pre-safe cycle life confidence level that causes test to provide is not high, exists and uses potential safety hazard.
Summary of the invention
The object of the invention is to the problems referred to above that exist for existing aero-engine compressor blade fatigue and cyclic test unit, a kind of aero-engine compressor blade fatigue and cyclic test unit is provided, the low cyclic loading of centrifugal force and high frequency load that this test unit can bear for simulation compressor blade when work, for solve the predetermined safe cycle life confidence level that existing test unit and test method provide not high, exist the problem of use potential safety hazard that research technique is provided.
Technical scheme of the present invention is: a kind of aero-engine compressor blade fatigue and cyclic test unit, comprise centrifugal force charging assembly, the centrifugal force cyclic loading of bearing while being used for simulating aero-engine compressor blade working, this test unit also comprises dither charging assembly, the high frequency load of bearing when simulating aero-engine compressor blade working; Described dither charging assembly involving vibrations platform, fixedly support A and the fixing support B of centrifugal force charging assembly of compressor blade testpieces, wherein, shaking 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 web joint C.
Preferably, centrifugal force charging assembly is positioned at a side of compressor blade testpieces, and the opposite side of compressor blade testpieces is provided with balance stem assembly.
Preferably, one end of balance stem assembly is fixed on blade fixed base, and the other end is fixed on web joint B.
Preferably, centrifugal force charging assembly is fixed on the top of support B, and the bottom of support B is fixed on web joint D.
Preferably, centrifugal force charging assembly comprises web joint A, load bar, pressurized strut, sensor and load bar bearing, one end of load bar is connected with sensor one side by pressurized strut, the other end is fixed on web joint A, the opposite side of sensor is connected with the briquetting in being arranged on compressor blade testpieces pin-and-hole by fixed bar, fixed bar is sleeved in load bar bearing, and load bar bearing is positioned at the top of support B.
Preferably, fixed bar one end connecting sensor, the other end is connected with briquetting by load plate.
Preferably, load plate is connected with briquetting by wire rope, and the outer cover of wire rope is equipped with the collar.
Beneficial effect of the present invention is: the present invention is simple in structure, easy to operate, under test condition, by the centrifugal force charging assembly and the dither charging assembly that arrange, the low cyclic loading of centrifugal force and the high frequency load of in the time of can simulating compressor blade work, bearing, make trystate and actual working state in full accord, realize centrifugal force load test and the high frequency load test of compressor blade, provide safe and reliable predetermined safe cycle life, avoided use potential safety hazard, solved the predetermined safe cycle life confidence level that existing test method provides not high, there is the problem of using potential safety hazard.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is vertical view of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
A kind of aero-engine compressor blade fatigue and cyclic test unit provided by the invention, comprise centrifugal force charging assembly, the centrifugal force cyclic loading of bearing while being used for simulating aero-engine compressor blade working, this test unit also comprises dither charging assembly, the high frequency load of bearing when simulating aero-engine compressor blade working; Described dither charging assembly involving vibrations platform 15, fixedly support A13 and the fixing support B16 of centrifugal force charging assembly of compressor blade testpieces 8, wherein, shaking table 15 is for applying dither to compressor blade testpieces 8.
For the ease of compressor blade testpieces 8 is applied to corresponding load, compressor blade testpieces 8 is fixed on the top of support A13 by blade fixed base 10, and the bottom of support A is fixed on web joint C.
Centrifugal force charging assembly is positioned at a side of compressor blade testpieces 8, when centrifugal force charging assembly applies the low cyclic loading of centrifugal force to compressor blade testpieces 8, in order to prevent that compressor blade testpieces 8 single load bearings and support A13 from being forgotten about it, the opposite side of compressor blade testpieces 8 is provided with balance stem assembly 11, for balance, loads the moment that centrifugal force produces.
For balance loads the moment that centrifugal force produces, one end of above-mentioned balance stem assembly 11 is fixed on blade fixed base 10, and the other end is fixed on web joint B12.
Centrifugal force charging assembly is fixed on the top of support B16, and the bottom of support B16 is fixed on web joint D17.
Centrifugal force charging assembly comprises web joint A1, load bar 2, pressurized strut 3, sensor 4 and load bar bearing 5, one end of load bar 2 is connected with sensor 4 one sides by pressurized strut 3, the other end is fixed on web joint A1, the opposite side of sensor 4 is connected with the briquetting 9 in being arranged on compressor blade testpieces 8 pin-and-holes by fixed bar, fixed bar is sleeved in load bar bearing 5, load bar bearing 5 is positioned at the top of support B16, load bar bearing is for support and connection plate A1, load bar 2, pressurized strut 3 and sensor 4, and the direction that guarantees the power that pressurized strut applies is perpendicular to pressing machine blade testpieces 8 pin-and-hole axis.
In order to realize being connected between sensor 4 and briquetting 9, above-mentioned fixed bar one end connecting sensor 4, the other end is connected with briquetting 9 by load plate 18.
For direction and the size that guarantees that centrifugal force loads, above-mentioned load plate 18 is connected with briquetting 9 by two wire rope 6, and in order further to guarantee the direction that centrifugal force loads, the outer cover of above-mentioned wire rope 6 is equipped with the collar 7.
Principle of work: when simulation provides the low cyclic loading of centrifugal force, pressurized strut 3 actions, during for engine operation, compressor blade testpieces 8 provides centrifugal force, and simulate low cyclic loading, the variation of centrifugal force is measured and monitored to sensor 4, when carrying out centrifugal force loading, by wire rope 6, guarantees the correct of centrifugal force loading directions and size, by the collar 7, two wire rope 6 are close together simultaneously, further guarantee that centrifugal force loading direction is correct; Balance stem assembly carries out balance to loading the moment of centrifugal force generation simultaneously, prevents that compressor blade testpieces 8 single load bearings and support A from being forgotten about it.
When simulation provides high frequency load, 15 pairs of compressor blade testpieces 8 of shaking table apply dither.
Claims (8)
1. an aero-engine compressor blade fatigue and cyclic test unit, comprise centrifugal force charging assembly, the centrifugal force cyclic loading of bearing while being used for simulating aero-engine compressor blade working, it is characterized in that: this test unit also comprises dither charging assembly the high frequency load of bearing when simulating aero-engine compressor blade working; Described dither charging assembly involving vibrations platform (15), fixedly support A (13) and the fixing support B (16) of centrifugal force charging assembly of compressor blade testpieces (8), wherein, shaking table (15) is for applying dither to compressor blade testpieces.
2. aero-engine compressor blade fatigue and cyclic test unit according to claim 1, it is characterized in that: compressor blade testpieces (8) is fixed on the top of support A (13) by blade fixed base (10), the bottom of support A (13) is fixed on web joint C (14).
3. aero-engine compressor blade fatigue and cyclic test unit according to claim 1, it is characterized in that: centrifugal force charging assembly is positioned at a side of compressor blade testpieces (8), the opposite side of compressor blade testpieces (8) is provided with balance stem assembly (11).
4. aero-engine compressor blade fatigue and cyclic test unit according to claim 3, is characterized in that: it is upper that blade fixed base (10) is fixed in one end of balance stem assembly (11), and the other end is fixed on web joint B (12).
5. aero-engine compressor blade fatigue and cyclic test unit according to claim 1, is characterized in that: centrifugal force charging assembly is fixed on the top of support B (16), and the bottom of support B (16) is fixed on web joint D (17).
6. according to the aero-engine compressor blade fatigue and cyclic test unit described in claim 1 to 5 any one, it is characterized in that: centrifugal force charging assembly comprises web joint A (1), load bar (2), pressurized strut (3), sensor (4) and load bar bearing (5), one end of load bar (2) is connected with sensor (4) one sides by pressurized strut (3), the other end is fixed on web joint A (1), the opposite side of sensor (4) is connected with the briquetting (9) in being arranged on compressor blade testpieces (8) pin-and-hole by fixed bar, fixed bar is sleeved in load bar bearing (5), load bar bearing (5) is positioned at the top of support B (16).
7. aero-engine compressor blade fatigue and cyclic test unit according to claim 6, is characterized in that: fixed bar one end connecting sensor (4), the other end is connected with briquetting (9) by load plate (18).
8. aero-engine compressor blade fatigue and cyclic test unit according to claim 7, it is characterized in that: load plate (18) is connected with briquetting (9) by wire rope (6), and the outer cover of 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 |
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| CN104062104A true CN104062104A (en) | 2014-09-24 |
| CN104062104B CN104062104B (en) | 2016-12-28 |
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| 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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Cited By (17)
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| CN104748930A (en) * | 2015-04-13 | 2015-07-01 | 东北大学 | Piezoelectric high-frequency vibration system used for high-order vibration fatigue testing of small-size components |
| CN106370369A (en) * | 2016-08-16 | 2017-02-01 | 中国航空工业集团公司沈阳发动机设计研究所 | High frequency gas excitation tester |
| CN106525365A (en) * | 2016-10-28 | 2017-03-22 | 中航动力股份有限公司 | Aeroengine wheel disc crack prefabrication test system and test method |
| 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 |
| 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 |
| 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 |
| CN108036911A (en) * | 2017-12-13 | 2018-05-15 | 中国飞机强度研究所 | A kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect |
| CN108168894A (en) * | 2017-12-13 | 2018-06-15 | 中国飞机强度研究所 | A kind of method for simulating turbine rotor blade centrifugal force |
| 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 |
| CN108931349A (en) * | 2018-04-09 | 2018-12-04 | 南京航空航天大学 | For simulating whirling test device in the hard object impact test of high speed |
| CN109238615A (en) * | 2018-11-05 | 2019-01-18 | 苏州东菱振动试验仪器有限公司 | A kind of device, method and the electromagnetic vibration generator system of equilibrium centrifugation power |
| CN109900461A (en) * | 2019-02-27 | 2019-06-18 | 东软医疗***股份有限公司 | A kind of CT swivel plate method for testing security and device |
| CN110006636A (en) * | 2019-03-15 | 2019-07-12 | 南京航空航天大学 | A kind of FOD repeated bend test part and its design method |
| CN111579191A (en) * | 2020-04-27 | 2020-08-25 | 南京航空航天大学 | Static target plate impact test device with electromagnetic loading and simulated centrifugal force effect and control method |
| CN111649926A (en) * | 2020-06-08 | 2020-09-11 | 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 |
| CN116754208A (en) * | 2023-08-16 | 2023-09-15 | 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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Cited By (23)
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| CN104748930A (en) * | 2015-04-13 | 2015-07-01 | 东北大学 | Piezoelectric high-frequency vibration system used for high-order vibration fatigue testing of small-size components |
| CN106370369B (en) * | 2016-08-16 | 2019-02-05 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of high-frequency gas excitation exerciser |
| CN106370369A (en) * | 2016-08-16 | 2017-02-01 | 中国航空工业集团公司沈阳发动机设计研究所 | High frequency gas excitation tester |
| 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 |
| CN106525365A (en) * | 2016-10-28 | 2017-03-22 | 中航动力股份有限公司 | Aeroengine wheel disc crack prefabrication test system and test method |
| CN106525365B (en) * | 2016-10-28 | 2019-01-04 | 中航动力股份有限公司 | A kind of aero-engine wheel disc crackle gives pilot system and test method processed |
| 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 |
| 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 |
| CN108036911A (en) * | 2017-12-13 | 2018-05-15 | 中国飞机强度研究所 | A kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect |
| CN108168894A (en) * | 2017-12-13 | 2018-06-15 | 中国飞机强度研究所 | A kind of method for simulating turbine rotor blade centrifugal force |
| 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 |
| CN108931349A (en) * | 2018-04-09 | 2018-12-04 | 南京航空航天大学 | For simulating whirling test device in the hard object impact test of high speed |
| 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 |
| CN109238615A (en) * | 2018-11-05 | 2019-01-18 | 苏州东菱振动试验仪器有限公司 | A kind of device, method and the electromagnetic vibration generator system of equilibrium centrifugation power |
| 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 |
| CN109900461A (en) * | 2019-02-27 | 2019-06-18 | 东软医疗***股份有限公司 | A kind of CT swivel plate method for testing security and device |
| CN110006636A (en) * | 2019-03-15 | 2019-07-12 | 南京航空航天大学 | A kind of FOD repeated bend test part and its design method |
| CN111579191A (en) * | 2020-04-27 | 2020-08-25 | 南京航空航天大学 | Static target plate impact test device with electromagnetic loading and simulated centrifugal force effect and control method |
| CN111649926A (en) * | 2020-06-08 | 2020-09-11 | 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 |
| CN116754208A (en) * | 2023-08-16 | 2023-09-15 | 天津航天瑞莱科技有限公司 | Fatigue test device for static blade adjusting mechanism assembly of compressor |
| 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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