CN105571802A - Testing method and testing device for blade pretightening force - Google Patents
Testing method and testing device for blade pretightening force Download PDFInfo
- Publication number
- CN105571802A CN105571802A CN201610065890.3A CN201610065890A CN105571802A CN 105571802 A CN105571802 A CN 105571802A CN 201610065890 A CN201610065890 A CN 201610065890A CN 105571802 A CN105571802 A CN 105571802A
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- blade
- electric vibration
- pretightning force
- vibration table
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention relates to a testing device for a blade pretightening force and a testing method for testing the pretightening force by means of the testing device. The testing device comprises an electric vibration platform which supplies vibrations to a blade, and a laser sensor which tests the amplitude of the blade. The electric vibration platform is provided with a clamp for fixing the blade. The electric vibration platform is provided with an acceleration sensor which tests platform surface amplitude of the electric vibration platform. The acceleration sensor and the laser sensor are electrically connected with a controller which controls the electric vibration platform. The clamp comprises a clamp body. The clamp body is provided with a mortise which penetrates through from one end to the other end and matches a blade tenon at the root of the blade, and a pushing trough which is communicated with the mortise and is used for placing a pushing block. One side of the clamp body is provided with a bolt hole which is perpendicular with and is communicated with the pushing trough. The bolt hole is internally provided with a bolt which supplies a pretightening force to the blade. According to the testing method and the testing device, the pretightening force is applied through the bolt, thereby simulating an eccentric force for fixing the blade and the clamp. Testing is performed in a vibration environment which is highly approximate to the real working condition of the blade, thereby obtaining true and effective testing data.
Description
Technical field
The invention belongs to environmental test field, particularly relate to a kind of method of testing to blade of aviation engine pretightning force and device.
Background technology
Environmental test is the various equipment of simulation and the test of parts when real work under residing environmental baseline, judges to be equipped in the duty under actual working conditions and endurance life by testing.Environment comprises mechanical environment, climatic environment and weather environment, and mechanical environment refers to various mechanical environment, and as vibration, impact and wave, climatic environment refers to high and low temperature environment and humidity environment etc., and weather environment refers to illumination, infrabar, mould and salt fog etc.
Current blade of aviation engine pretightning force test utilizes shaking table to test, that test data is effectively crucial at the true clamping of test process Leaf, the clamping of existing blade pretightning force test utilizes tongue-and-groove to be fixed blade, tenon groove structure on fixture is divided into upper and lower two parts, by lock-screw, blade is fixed, though the method can utilize the tenon of root of blade to be fixed by blade, but there is very large difference with the real working condition of blade of aviation engine, blade of aviation engine is by leaf disc spins band moving vane when real work, blade fixes by centrifugal force, in order to simulate the pretightning force test of blade of aviation engine under height emulation operating mode, develop a set of can be applicable to blade of aviation engine pretightning force test device necessary.
Summary of the invention
For solving the problems of the technologies described above, the object of this invention is to provide a kind of simulate centrifugal force fixed blade with the proving installation of Reality simulation operating mode and utilize this device height emulation operating mode under blade pretightning force method of testing.
The method of testing of blade pretightning force of the present invention, comprises step:
(1) the leaf tenon of root of blade being fixed on one is placed in the tongue-and-groove of the fixture on electric vibration table, bolt is utilized to pass described fixture and described leaf tenon offsets to provide pretightning force to described blade, there is provided one just to the laser sensor of described blade, and on described electric vibration table, an acceleration transducer is installed, and the signal that described acceleration transducer and described laser sensor export is inputted carries out in the controller vibrated in order to control described electric vibration table;
(2) described blade the first amplitude is under vibrating conditions tested with described laser sensor, test the second amplitude of described electric vibration platform top with described acceleration transducer, described controller reflects the change of described blade resonance frequency according to the change of the Amplitude Ration of the first amplitude and the second amplitude;
(3) pretightning force regulating described bolt to provide described blade gradually, when resonant frequency from low to high until constant time, pretightning force has reached required force value.
Further, described controller is vibrated by electric vibration table described in power amplifier control.
Further, described controller is also by the cooling unit of electric vibration table described in described power amplifier control.
The proving installation of blade pretightning force of the present invention, comprise and provide the electric vibration table of vibration to described blade and test the laser sensor of described blade amplitude, described electric vibration table is provided with the fixture of fixing described blade, described electric vibration table is provided with the acceleration transducer of its table top amplitude of test, described acceleration transducer and described laser sensor are electrically connected with the controller controlling described electric vibration table; Described fixture comprises chuck body, described chuck body is provided with and is through to the other end and the tongue-and-groove mated with the leaf tenon of described root of blade from its one end, and be communicated with described tongue-and-groove, for placing the inverted draw cut of jacking block, described chuck body side is provided with the bolt hole that be also communicated with vertical with described inverted draw cut, is provided with the bolt described blade being provided to pretightning force in described bolt hole.
Further, described chuck body is also provided with the lock-screw vertically running through described tongue-and-groove.
Further, described controller is vibrated by electric vibration table described in power amplifier control.
Further, described power amplifier is also connected with the cooling unit of described electric vibration table.
By such scheme, the present invention at least has the following advantages:
1, utilize bolt to apply pretightning force to blade, blade and fixture are fixed by simulation centrifugal force, and test under vibration, therefore, method of testing height of the present invention is close to the real working condition of blade, and the data of test are authentic and valid;
2, determine the method for testing of suitable pretightning force with the change of resonant frequency, can effectively improve control accuracy and measuring accuracy, guarantee the accuracy of test data;
3, proving installation of the present invention utilizes the leaf tenon of the tongue-and-groove on fixture to blade to be fixed, and provide pretightning force through fixture to leaf tenon by bolt, leaf tenon can be contacted completely with tongue-and-groove, when testing, leaf tenon is fixed in tongue-and-groove by the pretightning force that bolt provides, blade is the equal of fixed by centrifugal force, makes stress and the real work state consistency of blade, thus guarantees that the blade pretightning force recorded is authentic and valid;
4, owing to being subject to the effect of pretightning force at test process Leaf, proving installation of the present invention by arranging the lock-screw passing perpendicularly through tongue-and-groove on fixture, can prevent tongue-and-groove under the effect of pretightning force, producing distortion, avoid the surface of contact of leaf tenon and tongue-and-groove to change, thus guarantee that the pretightning force recorded is authentic and valid.
Above-mentioned explanation is only the general introduction of technical solution of the present invention, in order to better understand technological means of the present invention, and can be implemented according to the content of instructions, coordinates accompanying drawing to be described in detail as follows below with preferred embodiment of the present invention.
Accompanying drawing explanation
Fig. 1 is the structural representation of blade pretightning force proving installation of the present invention;
Fig. 2 is the structural representation that in blade pretightning force proving installation, fixture clamps blade;
Fig. 3 is the front view of fixture;
Fig. 4 is the side view of fixture;
Fig. 5 is the vertical view of fixture;
Electric vibration platform top acceleration change figure when Fig. 6 is test;
Fig. 7 is the variation diagram testing the blade resonance frequency arrived.
Embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
As shown in Figures 1 to 5, a kind of blade pretightning force proving installation described in a preferred embodiment of the present invention, comprising:
For providing exciting force to blade, and make blade in test process, keep the electric vibration table 1 of resonance state;
Clamp the fixture 2 of blade, fixture 2 comprises chuck body 10, chuck body 10 is provided with and is through to the other end from its one end and the tongue-and-groove 11 mated with the leaf tenon of blade 50 root and the inverted draw cut 12 be communicated with tongue-and-groove 11, inverted draw cut 12 is used for laying the jacking block 20 offseted with leaf tenon, chuck body 10 side is provided with the bolt hole 13 that be also communicated with vertical with inverted draw cut 12, lay the bolt 30 that pretightning force is provided by jacking block 20 pairs of leaf tenons in bolt hole 13, chuck body 10 is also provided with the lock-screw 40 vertically running through tongue-and-groove 11;
Just to the laser sensor 3 of blade, in order to pilot blade the first amplitude under vibrating conditions;
Be arranged on the acceleration transducer 4 on electric vibration table 1, in order to test the second amplitude of electric vibration table 1 table top;
Controller 5, receives the signal that acceleration transducer 4 exports with laser sensor 3, and processes signal, reflects the change of blade 50 resonant frequency according to the Amplitude Ration of the first amplitude and the second amplitude;
Power amplifier 6, amplifies the power that controller 5 exports, the power drive electric vibration table 1 after amplification and the cooling unit 7 of electric vibration table 1.
When utilizing fixture 2 to clamp blade, first in inverted draw cut 12, insert jacking block 20, bolt 30 is pressed on jacking block 20 through bolt hole 13, the leaf tenon of blade 50 is inserted in the tongue-and-groove 11 in chuck body 10, bolt 30 is locked, to provide pretightning force by jacking block 20 pairs of blades 50, the leaf tenon of blade 50 is fixed in tongue-and-groove 11 by simulation centrifugal force; Finally locked by two lock-screws 40, to prevent under the effect of pretightning force, tongue-and-groove 11 part is outwards out of shape, i.e. two lock-screws, 40 position-limiting actions, avoid tongue-and-groove 11 to be out of shape, guarantee that the leaf tenon of blade 50 root contacts completely with the tongue-and-groove 11 on fixture, to record authentic and valid pretightning force.
When utilizing proving installation of the present invention to carry out pretightning force test, first proving installation is installed and connect, leaf tenon by blade 50 root inserts in the tongue-and-groove 11 of the fixture be arranged on electric vibration table 1, bolt 30 is utilized to offset through fixture and leaf tenon, by laser sensor 3 just to blade 50, degree of will speed up sensor 4 to be arranged on electric vibration table 1, and the signal that degree of will speed up sensor 4 and laser sensor 3 export inputs and carries out in the controller 5 of frequency sweep in order to control electric vibration table 1; With laser sensor 3 pilot blade 50 the first amplitude under vibrating conditions, test the second amplitude of electric vibration table 1 table top with acceleration transducer 4, controller 5 reflects the change of blade 50 resonant frequency according to the change of the Amplitude Ration of the first amplitude and the second amplitude; The size of adjusting bolt 30 pairs of blade 50 pretightning forces gradually, namely the locking degree of bolt 30 is adjusted, with the pretightning force of resonant frequency determination bolt 30 pairs of blades 50 of blade 50, when blade 50 resonant frequency from low to high until constant time, pretightning force has reached required force value.
According to the mechanical characteristic of blade, suitable pretightning force can be determined with the change of blade resonance frequency, test data figure as shown in Figures 6 and 7.When pretightning force is not enough, the resonant frequency of blade can be on the low side, along with the leaf tenon of the increase root of blade of pretightning force and the tongue and groove joint credit union of fixture firm, the resonant frequency of blade can increase simultaneously, when blade resonant frequency not variable declaration pretightning force reached requirement (when namely starting to move to right when the curve in Fig. 7, illustrate that the resonant frequency of blade no longer changes), pretightning force is excessive, can cause the damage of blade.
The above is only the preferred embodiment of the present invention; be not limited to the present invention; should be understood that; for those skilled in the art; under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and modification, these improve and modification also should be considered as protection scope of the present invention.
Claims (7)
1. a method of testing for blade pretightning force, is characterized in that comprising step:
(1) the leaf tenon of root of blade being fixed on one is placed in the tongue-and-groove of the fixture on electric vibration table, bolt is utilized to pass described fixture and described leaf tenon offsets to provide pretightning force to described blade, there is provided one just to the laser sensor of described blade, and on described electric vibration table, an acceleration transducer is installed, and the signal that described acceleration transducer and described laser sensor export is inputted carries out in the controller vibrated in order to control described electric vibration table;
(2) described blade the first amplitude is under vibrating conditions tested with described laser sensor, test the second amplitude of described electric vibration platform top with described acceleration transducer, described controller reflects the change of described blade resonance frequency according to the change of the Amplitude Ration of the first amplitude and the second amplitude;
(3) pretightning force regulating described bolt to provide described blade gradually, when resonant frequency from low to high until constant time, pretightning force has reached required force value.
2. the method for testing of blade pretightning force according to claim 1, is characterized in that: described controller is vibrated by electric vibration table described in power amplifier control.
3. the method for testing of blade pretightning force according to claim 2, is characterized in that: described controller is also by the cooling unit of electric vibration table described in described power amplifier control.
4. the proving installation of a blade pretightning force, it is characterized in that: comprise and provide the electric vibration table of vibration to described blade and test the laser sensor of described blade amplitude, described electric vibration table is provided with the fixture of fixing described blade, described electric vibration table is provided with the acceleration transducer of its table top amplitude of test, described acceleration transducer and described laser sensor are electrically connected with the controller controlling described electric vibration table; Described fixture comprises chuck body, described chuck body is provided with and is through to the other end and the tongue-and-groove mated with the leaf tenon of described root of blade from its one end, and be communicated with described tongue-and-groove, for placing the inverted draw cut of jacking block, described chuck body side is provided with the bolt hole that be also communicated with vertical with described inverted draw cut, is provided with the bolt described blade being provided to pretightning force in described bolt hole.
5. the proving installation of blade pretightning force according to claim 4, is characterized in that: described chuck body is also provided with the lock-screw vertically running through described tongue-and-groove.
6. the proving installation of blade pretightning force according to claim 4, is characterized in that: described controller is vibrated by electric vibration table described in power amplifier control.
7. the proving installation of blade pretightning force according to claim 6, is characterized in that: described power amplifier is also connected with the cooling unit of described electric vibration table.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610065890.3A CN105571802B (en) | 2016-02-01 | 2016-02-01 | The method of testing of blade pretightning force |
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| CN201610065890.3A CN105571802B (en) | 2016-02-01 | 2016-02-01 | The method of testing of blade pretightning force |
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| CN105571802A true CN105571802A (en) | 2016-05-11 |
| CN105571802B CN105571802B (en) | 2018-01-16 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106226015A (en) * | 2016-07-01 | 2016-12-14 | 西北工业大学 | A kind of assay device of turbine disk coupled vibrations |
| CN106768755A (en) * | 2016-11-28 | 2017-05-31 | 中航动力股份有限公司 | A kind of fixture integrated and test method for swallow-tail form tenon turbine blade vibration fatigue test |
| CN107677441A (en) * | 2017-10-10 | 2018-02-09 | 上海汇博精工电子科技有限公司 | A kind of electric oscillation platform pilot system |
| 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 |
| CN108709624A (en) * | 2018-05-07 | 2018-10-26 | 南昌航空大学 | A kind of high-precision intrinsic frequency measurement method and device |
| CN110514378A (en) * | 2019-08-30 | 2019-11-29 | 中国航发动力股份有限公司 | A kind of engine band convex shoulder fan blade vibration fatigue test device |
| CN111256935A (en) * | 2020-03-31 | 2020-06-09 | 中国航发动力股份有限公司 | Blade vibration test method and vibration test tool |
| CN112504590A (en) * | 2020-11-05 | 2021-03-16 | 中国航发北京航空材料研究院 | Clamp for vibration fatigue test of aero-engine blade |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106226015A (en) * | 2016-07-01 | 2016-12-14 | 西北工业大学 | A kind of assay device of turbine disk coupled vibrations |
| CN106768755B (en) * | 2016-11-28 | 2019-10-01 | 中航动力股份有限公司 | A kind of fixture integrated and test method for swallow-tail form tenon turbine blade vibration fatigue test |
| CN106768755A (en) * | 2016-11-28 | 2017-05-31 | 中航动力股份有限公司 | A kind of fixture integrated and test method for swallow-tail form tenon turbine blade vibration fatigue test |
| CN107677441A (en) * | 2017-10-10 | 2018-02-09 | 上海汇博精工电子科技有限公司 | A kind of electric oscillation platform pilot system |
| 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 |
| CN108709624A (en) * | 2018-05-07 | 2018-10-26 | 南昌航空大学 | A kind of high-precision intrinsic frequency measurement method and device |
| CN108709624B (en) * | 2018-05-07 | 2020-05-15 | 南昌航空大学 | High-precision natural frequency measuring method and device |
| CN110514378A (en) * | 2019-08-30 | 2019-11-29 | 中国航发动力股份有限公司 | A kind of engine band convex shoulder fan blade vibration fatigue test device |
| CN110514378B (en) * | 2019-08-30 | 2021-11-30 | 中国航发动力股份有限公司 | Vibration fatigue test device for fan blade with convex shoulder of engine |
| CN111256935A (en) * | 2020-03-31 | 2020-06-09 | 中国航发动力股份有限公司 | Blade vibration test method and vibration test tool |
| CN111256935B (en) * | 2020-03-31 | 2022-04-26 | 中国航发动力股份有限公司 | Blade vibration test method and vibration test tool |
| CN112504590A (en) * | 2020-11-05 | 2021-03-16 | 中国航发北京航空材料研究院 | Clamp for vibration fatigue test of aero-engine blade |
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