CN102954887A - Testing device for measuring damping effect of working blades of high-pressure turbine - Google Patents
Testing device for measuring damping effect of working blades of high-pressure turbine Download PDFInfo
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- CN102954887A CN102954887A CN2012104423646A CN201210442364A CN102954887A CN 102954887 A CN102954887 A CN 102954887A CN 2012104423646 A CN2012104423646 A CN 2012104423646A CN 201210442364 A CN201210442364 A CN 201210442364A CN 102954887 A CN102954887 A CN 102954887A
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- rocker arm
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Abstract
The invention discloses a testing device for measuring a damping effect of working blades of a high-pressure turbine. The testing device comprises a stationary fixture, a fixture frame, a support, a pin shaft, a long rocker arm, a short rocker arm, a force applying bolt, force transmission arms, a front baffle plate, a rear baffle plate, a top block, weights, the working blades and a locking plate, wherein the working blades are arranged on the stationary fixture, the stationary fixture is pressed in the fixture frame through a nut, the short rocker arm is embedded and sleeved at the inner part of the long rocker arm, and the short rocker arm and the long rocker arm are commonly arranged on the pin shaft; the weights are respectively suspended at the positions of grooves of the long rocker arm and the short rocker arm, the other ends of the long rocker arm and the short rocker arm are respectively contacted with one force transmission arm by being used as force applying devices of a system, and force can be transmitted to a damping fin arranged between the two blades; and the front baffle plate, the stationary fixture and the rear baffle plate are fixedly arranged together through bolts. The testing device disclosed by the invention has the advantages that the structure is simple, the force bearing situation of the working blades of the high-pressure turbine during the working of an engine can be fully simulated, and guarantees are provided for the research on the safety performance and the reliability of the engine.
Description
Technical field
The present invention relates to the test unit field of high-pressure turbine working blade, particularly a kind of test unit of measuring the high-pressure turbine working blade damping.
Background technology
Existing high-pressure turbine working blade damping test unit can only carry out vibration survey to single high-pressure turbine working blade, and can not simulate centrifugal force that damping block or locking plate produce to high-pressure turbine working blade lower stress situation in working order.Can only obtain the damping data of single high-pressure turbine working blade with the high-pressure turbine working blade damping of existing test unit measurement, the damping rule of the high-pressure turbine working blade that can not more be tallied with the actual situation is unfavorable for the damping block design and researchp of engine high pressure turbine work.
Summary of the invention
The present invention seeks to the limitation for existing high-pressure turbine damping measurement mechanism, the spy provides a kind of test unit of measuring the high-pressure turbine working blade damping.
The invention provides a kind of test unit of measuring the high-pressure turbine working blade damping, it is characterized in that: the test unit of described measurement high-pressure turbine working blade damping comprises stationary fixture 1, jig frame 2, support 3, bearing pin 4, long Rocker arm 5, short rocker arm| 6, application of force bolt 8, power transmission arm 9, front apron 10, backboard 11, jacking block 12, counterweight 13, working-blade 14 and locking plate 15;
Working-blade 14 is installed on the stationary fixture 1, and stationary fixture 1 is pressed in the jig frame 2 by nut, and short rocker arm| 6 is nested in the inside of long Rocker arm 5, jointly is installed on the bearing pin 4 with long Rocker arm 5, and bearing pin 4 adopts interference fit with the hole on the support 3; Counterweight 13 is hung in the groove of long Rocker arm 5 and short rocker arm| 6, and as the force application apparatus of system, each contacts the other end of long Rocker arm 5 and short rocker arm| 6 with a power transmission arm 9, and power is passed to damping fin between two blades; Front apron 10 and backboard 11 are the actual conditions of simulating as required and the structure that designs, and application of force bolt 8 passes to locking plate 15 by the jacking block 12 of " L " shape with power; Front apron 10, stationary fixture 1, backboard 12 threes be bolted on together.
The stationary fixture 1 that is used for installment work blade 14 has three tongue-and-grooves, and three working-blades can be installed simultaneously.
Bearing pin 4 adopts the mode of interference fit to be fixed in the circular hole of support 3, and it is inner that short rocker arm| 6 is nested in long Rocker arm 5, and both by bearing pin 4, can freely swing at bearing pin simultaneously; The groove place that counterweight 13 is installed in respectively short rocker arm| 6 and long Rocker arm 5 carries out the application of force, realizes different stress loads by installing different counterweights 13 weight additional.
The application of force of 8 pairs of locking plates 15 of application of force bolt adopts the mode of the indirect application of force of bolt tightening; Produce displacement when application of force bolt 8 is tightened, promote jacking block 12, jacking block 12 extruding locking plates 15, thereby to locking plate 15 application of forces.
Two power transmission arms 9 contact with long Rocker arm 5 and short rocker arm| 6 respectively, thereby obtain the different power from counterweight.
In order to implement better the present invention, further, be equipped with reinforcement between 6, two swing arms of described long Rocker arm 5 and short rocker arm|.In addition, rocking arm is installed counterweight one side should be provided with the groove that special suspension counterweight lifting rope is used, and the groove two ends arrange semicircle gap.
In order to implement better the present invention, further, above-mentioned stationary fixture 1 has three tongue-and-grooves, and the tongue-and-groove size should cooperate with tested high-pressure turbine working blade
In order to implement better the present invention, further, above-mentioned jig frame 2 is designed with bolt hole, by tighting a bolt the anchor clamps 1 that are fixedly clamped, thereby realize the firm fixing of stationary fixture 1 and high-pressure turbine working blade, in order to make stationary fixture 1 when clamping working-blade 14, have elasticity, have waist type groove on the stationary fixture 1.
In order to implement better the present invention, further, above-mentioned application of force bolt 8 should make right angle, jacking block 12 outside aim at application of force bolt 8 axis to jacking block 12 application of force time.
Counterweight passes to two interlobate damping simulated blocks by long and short rocking arm with power, in the time of can being used for analog operation damping fin centrifugal force.Application of force bolt by jacking block to the locking plate application of force, the centrifugal force of locking plate in the time of can analog operation.
Advantage of the present invention:
The present invention is simple in structure, and the abundant stressing conditions of simulated engine when work high-pressure turbine working blade is for the research of engine health, reliability provides guarantee.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
Fig. 1 is for measuring the test unit synoptic diagram of high-pressure turbine working blade damping;
Fig. 2 is damping test device force transmission mechanism synoptic diagram;
Fig. 3 is damping test device anchor clamps master apparent direction synoptic diagram;
Fig. 4 is the left apparent direction synoptic diagram of damping test device anchor clamps.
Embodiment
Present embodiment provides a kind of test unit of measuring the high-pressure turbine working blade damping, it is characterized in that: the test unit of described measurement high-pressure turbine working blade damping comprises stationary fixture 1, jig frame 2, support 3, bearing pin 4, long Rocker arm 5, short rocker arm| 6, application of force bolt 8, power transmission arm 9, front apron 10, backboard 11, jacking block 12, counterweight 13, working-blade 14 and locking plate 15;
Working-blade 14 is installed on the stationary fixture 1, and stationary fixture is pressed in the jig frame 2 by nut, and short rocker arm| 6 is nested in the inside of long Rocker arm 5, jointly is installed on the bearing pin 4 with long Rocker arm 5, and bearing pin 4 adopts interference fit with the hole on the support 3; Counterweight 13 is hung in the groove of long Rocker arm 5 and short rocker arm| 6, and as the force application apparatus of system, each contacts the other end of long Rocker arm 5 and short rocker arm| 6 with a power transmission arm 9, and power is passed to damping fin between two blades; Front apron 10 and backboard 11 are the actual conditions of simulating as required and the structure that designs, and application of force bolt 8 passes to locking plate 15 by the jacking block 12 of " L " shape with power; Front apron 10, stationary fixture 1, backboard 12 threes be bolted on together.
The stationary fixture 1 that is used for installment work blade 14 has three tongue-and-grooves, and three working-blades can be installed simultaneously.
Bearing pin 4 adopts the mode of interference fit to be fixed in the circular hole of support 3, and it is inner that short rocker arm| 6 is nested in long Rocker arm 5, and both by bearing pin 4, can freely swing at bearing pin simultaneously; The groove place that counterweight 13 is installed in respectively short rocker arm| 6 and long Rocker arm 5 carries out the application of force, realizes different stress loads by installing different counterweights 13 weight additional.
The application of force of 8 pairs of locking plates 15 of application of force bolt adopts the mode of the indirect application of force of bolt tightening; Produce displacement when application of force bolt 8 is tightened, promote jacking block 12, jacking block 12 extruding locking plates 15, thereby to locking plate 15 application of forces.
Two power transmission arms 9 contact with long Rocker arm 5 and short rocker arm| 6 respectively, thereby obtain the different power from counterweight.
In order to implement better present embodiment, further, be equipped with reinforcement between 6, two swing arms of described long Rocker arm 5 and short rocker arm|.In addition, rocking arm is installed counterweight one side should be provided with the groove that special suspension counterweight lifting rope is used, and the groove two ends arrange semicircle gap.
In order to implement better present embodiment, further, above-mentioned stationary fixture 1 has three tongue-and-grooves, and the tongue-and-groove size should cooperate with tested high-pressure turbine working blade
In order to implement better present embodiment, further, above-mentioned jig frame 2 is designed with bolt hole, by tighting a bolt the anchor clamps 1 that are fixedly clamped, thereby realize the firm fixing of stationary fixture 1 and high-pressure turbine working blade, for stationary fixture 1 has elasticity, have waist type groove on the stationary fixture 1.
In order to implement better present embodiment, further, above-mentioned application of force bolt 8 should make right angle, jacking block 12 outside aim at application of force bolt 8 axis to jacking block 12 application of force time.
Counterweight passes to two interlobate damping simulated blocks by long and short rocking arm with power, in the time of can being used for analog operation damping fin centrifugal force.Application of force bolt by jacking block to the locking plate application of force, the centrifugal force of locking plate in the time of can analog operation.
Claims (6)
1. test unit of measuring the high-pressure turbine working blade damping, it is characterized in that: the test unit of described measurement high-pressure turbine working blade damping comprises stationary fixture (1), jig frame (2), support (3), bearing pin (4), long rocking arm (5), short rocker arm| (6), application of force bolt (8), power transmission arm (9), front apron (10), backboard (11), jacking block (12), counterweight (13), working-blade (14) and locking plate (15);
Working-blade (14) is installed on the stationary fixture (1), stationary fixture is pressed in the jig frame (2) by nut, short rocker arm| (6) is nested in the inside of long rocking arm (5), jointly be installed on the bearing pin (4) with long rocking arm (5), bearing pin (4) adopts interference fit with the hole on the support (3); Counterweight (13) is hung in the groove of long rocking arm (5) and short rocker arm| (6), and as the force application apparatus of system, each contacts the other end of long rocking arm (5) and short rocker arm| (6) with a power transmission arm (9), and power is passed to damping fin between two blades; Front apron (10) and backboard (11) are the actual conditions of simulating as required and the structure that designs, and application of force bolt (8) passes to locking plate (15) by the jacking block (12) of " L " shape with power; Front apron (10), stationary fixture (1), backboard (12) three is bolted on together.
2. the test unit of measurement high-pressure turbine working blade damping according to claim 1 is characterized in that: the stationary fixture (1) that is used for installment work blade (14) has three tongue-and-grooves, and three working-blades can be installed simultaneously.
3. the test unit of measurement high-pressure turbine working blade damping according to claim 1, it is characterized in that: bearing pin (4) adopts the mode of interference fit to be fixed in the circular hole of support (3), short rocker arm| (6) is nested in long rocking arm (5) inside, both by bearing pin (4), can freely swing at bearing pin simultaneously; The groove place that counterweight (13) is installed in respectively short rocker arm| (6) and long rocking arm (5) carries out the application of force, realizes different stress loads by installing different counterweight (13) weight additional.
4. the test unit of measurement high-pressure turbine working blade damping according to claim 1 is characterized in that: application of force bolt (8) adopts the mode of the indirect application of force of bolt tightening to the application of force of locking plate (15); Application of force bolt (8) produces displacement when tightening, promote jacking block (12), jacking block (12) extruding locking plate (15), thereby to locking plate (15) application of force.
5. the test unit of measurement high-pressure turbine working blade damping according to claim 1, it is characterized in that: jacking block (12) shape facility is L-type, have groove at backboard (11), jacking block (12) is embedded in the groove of backboard (11), guarantees that jacking block (12) is freely up and down.
6. the test unit of measurement high-pressure turbine working blade damping according to claim 1, it is characterized in that: two power transmission arms (9) contact with long rocking arm (5) and short rocker arm| (6) respectively, thereby obtain the different power from counterweight.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210442364.6A CN102954887B (en) | 2012-11-08 | 2012-11-08 | A kind of test unit measuring high-pressure turbine working blade damping |
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| CN201210442364.6A CN102954887B (en) | 2012-11-08 | 2012-11-08 | A kind of test unit measuring high-pressure turbine working blade damping |
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| CN102954887A true CN102954887A (en) | 2013-03-06 |
| CN102954887B CN102954887B (en) | 2016-03-30 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106813915A (en) * | 2017-02-09 | 2017-06-09 | 北京航空航天大学 | Pad loading device and damping test device between a kind of blade loading device, groove |
| 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 |
| CN117536692A (en) * | 2024-01-09 | 2024-02-09 | 中国航发沈阳发动机研究所 | Turbine rotor blade damping sealing structure and interference calculation method thereof |
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| US6085593A (en) * | 1997-09-04 | 2000-07-11 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Vibration damping element test apparatus |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| CN101660989A (en) * | 2008-08-25 | 2010-03-03 | 中国船舶重工集团公司第七○三研究所 | Inching corrosion wear test machine |
| CN102156035A (en) * | 2011-03-24 | 2011-08-17 | 西安交通大学 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
| RU110483U1 (en) * | 2011-05-26 | 2011-11-20 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | DEVICE FOR RESEARCH OF DAMPING ABILITY OF TURBINE SHOULDERS WITH FRICTION DUMPERS |
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2012
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6085593A (en) * | 1997-09-04 | 2000-07-11 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Vibration damping element test apparatus |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| CN101660989A (en) * | 2008-08-25 | 2010-03-03 | 中国船舶重工集团公司第七○三研究所 | Inching corrosion wear test machine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106813915A (en) * | 2017-02-09 | 2017-06-09 | 北京航空航天大学 | Pad loading device and damping test device between a kind of blade loading device, groove |
| CN106813915B (en) * | 2017-02-09 | 2018-05-15 | 北京航空航天大学 | Gasket loading device and damping test device between a kind of blade loading device, groove |
| 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 |
| 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 |
| CN117536692A (en) * | 2024-01-09 | 2024-02-09 | 中国航发沈阳发动机研究所 | Turbine rotor blade damping sealing structure and interference calculation method thereof |
| CN117536692B (en) * | 2024-01-09 | 2024-04-09 | 中国航发沈阳发动机研究所 | Turbine rotor blade damping sealing structure and interference calculation method thereof |
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| CN102954887B (en) | 2016-03-30 |
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