CN107941607A - Suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test - Google Patents
Suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test Download PDFInfo
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- CN107941607A CN107941607A CN201711429496.4A CN201711429496A CN107941607A CN 107941607 A CN107941607 A CN 107941607A CN 201711429496 A CN201711429496 A CN 201711429496A CN 107941607 A CN107941607 A CN 107941607A
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- loose piece
- pressure turbine
- clamping device
- turbine blade
- clamping
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
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- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
In order to solve existing gripping apparatus grips poor reliability, so that the problem of influencing high-pressure turbine blade high-cycle fatigue test, a kind of clamping device suitable for big rigidity high-pressure turbine blade high-cycle fatigue test is proposed.Including base 1, band tongue-and-groove loose piece 2, Top fastening screw 3, attachment screw 5 and listrium clamping loose piece 6；High-pressure turbine blade tenon to be tested loads in band tongue-and-groove loose piece 2, held out against by 3 radial direction of Top fastening screw, band tongue-and-groove loose piece 2 loads base 1 bottom-up, and listrium clamping loose piece 6 is connected with base 1 by attachment screw 5, finally clamping device is integrally attached on horizontal vibration platform；Damaged when blade is tested in order to prevent, cushion block 4 is set between Top fastening screw 3 and high-pressure turbine blade.
Description
Technical field
The invention belongs to blade of aviation engine testing equipment design field, and in particular to high-pressure turbine blade high week
The clamping device of fatigue test.
Background technology
The anti-high cycle fatigue design of aerial motor spare part has become the key technology for restricting high-performance enginer development
One of, wherein, the high cycle fatigue crack failure problems for the turbo blade being operated in high temperature combustion environment are especially notable.Carry out whirlpool
The anti-high cycle fatigue design of impeller blade, most important link are then by carrying out the high-cycle fatigue test under hot conditions, obtaining leaf
The high cycle fatigue performance of sheet element reality.
Aero-engine high-pressure turbine blade structural rigidity is big, as shown in Figure 1, to blade tenon head during high-cycle fatigue test
The reliable retention difficulty of position is larger, and traditional clamping device is made of pedestal, loose piece and screw, as shown in Fig. 2, this device is difficult
To ensure to keep the reliable retention to blade tenon in the high-cycle fatigue test for a long time and under the conditions of heating, can not pass through
Experiment obtains the Temperature High Cycle Fatigue performance of high-pressure turbine blade component.
The content of the invention
Goal of the invention, in order to solve existing gripping apparatus grips poor reliability, so that it is tired to influence high-pressure turbine blade high week
The problem of labor is tested, proposes a kind of clamping device suitable for big rigidity high-pressure turbine blade high-cycle fatigue test.
Technical solution
A kind of clamping device suitable for big rigidity high-pressure turbine blade high-cycle fatigue test, including base 1, band tongue-and-groove are lived
Block 2, Top fastening screw 3, attachment screw 5 and listrium clamping loose piece 6；High-pressure turbine blade tenon to be tested loads band tongue-and-groove loose piece
In 2, held out against by 3 radial direction of Top fastening screw, band tongue-and-groove loose piece 2 loads base 1 bottom-up, and listrium clamping loose piece 6 passes through company
Connect screw 5 to be connected with base 1, finally clamping device is integrally attached on horizontal vibration platform；When blade is tested in order to prevent
Damage, sets cushion block 4 between Top fastening screw 3 and high-pressure turbine blade.
Beneficial effect：A kind of clamping device suitable for big rigidity high-pressure turbine blade high-cycle fatigue test, clamping dress
Put it is middle provide circumferential and radially clamping rigidity key structure part by heat influenced it is smaller, heating and it is long when operating condition under
It still is able to ensure the reliability of clamping, which is applicable to the blade high-cycle fatigue test under the conditions of heating；Band at the same time
Tongue-and-groove loose piece and listrium clamping loose piece employ replaceable design, and the clamping to different leaves can be realized by replacement,
Economy is improved, easily appearance loosening, result of the test dispersiveness are big and right for clamping during solving conventional brace experiment
Pilot blade causes the problems such as Abnormal damage.
Brief description of the drawings
Fig. 1 is typical high voltage turbine blade arrangement schematic diagram；
Fig. 2 is traditional turbo blade fatigue test clamp structure；
Fig. 3 is clamping device top view proposed by the present invention；
Fig. 4 is clamping device sectional view proposed by the present invention；
Number explanation：1- bases, 2- band tongue-and-grooves loose piece, 3- Top fastening screws, 4- cushion blocks, 5- attachment screws, the clamping of 6- listriums
Loose piece.
Embodiment
High-pressure turbine blade to be tested loads band tongue-and-groove loose piece 2, is held out against by 3 radial direction of Top fastening screw, in Top fastening screw 3
Set cushion block 4, to ensure that vane stress is uniform, prevent damaged blade between high-pressure turbine blade, band tongue-and-groove loose piece 2 is from inside
Load base 1, base 1 is connected by screw and tightens with horizontal vibration slide unit, and band tongue-and-groove loose piece 2 is carried with 1 mounting surface of base
Certain established angle, the wedge effect produced by the Interference contact with tongue-and-groove loose piece 2 and horizontal vibration platform surface realize week
To compression, using the teaching of the invention it is possible to provide enough circumferential clamping rigidity, and can keep reliable and stable at a warm condition.
Dismountable turbo blade listrium clamping loose piece 6 is provided with above clamping device, listrium clamping loose piece 6 passes through connection
Screw 5 is connected with base 1, and the clamping to blade listrium is realized by wedge effect, further improves the circumferential direction clamping to blade
Rigidity.
On the basis of above-mentioned clamping device, the band tongue-and-groove loose piece 2 and listrium clamping loose piece 6 are replaceable set
Meter, can carry out corresponding replacement according to different turbine blade arrangement forms；Top fastening screw 3 can be according to blade radial chucking power need
Will, it is changed to and holds out against loose piece or hydraulic mandril with certain interference volume.
Claims (4)
1. suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test, it is characterised in that：The device includes bottom
Seat (1), band tongue-and-groove loose piece (2), Top fastening screw (3), attachment screw (5) and listrium clamping loose piece (6)；High-pressure turbine to be tested
Blade tenon loads in band tongue-and-groove loose piece (2), is radially held out against by Top fastening screw (3), and band tongue-and-groove loose piece (2) fills bottom-up
Enter base (1), listrium clamping loose piece (6) is connected with base (1) by attachment screw (5), finally integrally fixes clamping device
On horizontal vibration platform.
2. clamping device according to claim 1, its spy is：Top fastening screw (3) and high-pressure turbine blade tenon it
Between set cushion block (4).
3. clamping device according to claim 1, its spy is：The band tongue-and-groove loose piece (2) and listrium clamping loose piece (6)
It is replaceable.
4. clamping device according to claim 1, it is characterised in that：The Top fastening screw (3) is with being changed to certain interference
Amount holds out against loose piece or hydraulic mandril.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711429496.4A CN107941607A (en) | 2017-12-26 | 2017-12-26 | Suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711429496.4A CN107941607A (en) | 2017-12-26 | 2017-12-26 | Suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107941607A true CN107941607A (en) | 2018-04-20 |
Family
ID=61940236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711429496.4A Pending CN107941607A (en) | 2017-12-26 | 2017-12-26 | Suitable for the clamping device of big rigidity high-pressure turbine blade high-cycle fatigue test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107941607A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186908A (en) * | 2018-08-24 | 2019-01-11 | 北京航空航天大学 | The cooling clamping device of the high-temperature vibrating test of turbine guide vane |
| CN109682325A (en) * | 2018-11-27 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | Frustoconical bevel angle inspection, correcting device and method in aero-engine fuel nozzle body |
| CN110426171A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of fixture and its application method of turbine blade vibration fatigue test |
| 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 |
| CN112975758A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Blade tenon tooth protection device and tenon tooth protection method thereof |
| CN114112271A (en) * | 2021-11-30 | 2022-03-01 | 中国航发湖南动力机械研究所 | Turbine blade fatigue test fixture and device |
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| CN206235511U (en) * | 2016-12-12 | 2017-06-09 | 赵志武 | A kind of metal material detection clamp clamping device of clamp of replaceable gripping block |
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| CN2903967Y (en) * | 2006-01-20 | 2007-05-23 | 四川省瑞格尔仪器有限公司 | Arc wedge type drawing clamp |
| CN1865904A (en) * | 2006-06-15 | 2006-11-22 | 哈尔滨工业大学 | Sheet material compression clamp |
| CN201273030Y (en) * | 2008-11-05 | 2009-07-15 | 湖南省第六工程有限公司 | Portable steel stranded wire clamper |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186908A (en) * | 2018-08-24 | 2019-01-11 | 北京航空航天大学 | The cooling clamping device of the high-temperature vibrating test of turbine guide vane |
| CN109682325A (en) * | 2018-11-27 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | Frustoconical bevel angle inspection, correcting device and method in aero-engine fuel nozzle body |
| CN110426171A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of fixture and its application method of turbine blade vibration fatigue test |
| 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 |
| CN112975758A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Blade tenon tooth protection device and tenon tooth protection method thereof |
| CN114112271A (en) * | 2021-11-30 | 2022-03-01 | 中国航发湖南动力机械研究所 | Turbine blade fatigue test fixture and device |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180420 |
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| RJ01 | Rejection of invention patent application after publication |