CN207358923U - Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture - Google Patents
Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture Download PDFInfo
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- CN207358923U CN207358923U CN201721315180.8U CN201721315180U CN207358923U CN 207358923 U CN207358923 U CN 207358923U CN 201721315180 U CN201721315180 U CN 201721315180U CN 207358923 U CN207358923 U CN 207358923U
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- hold assembly
- disc type
- fatigue life
- test fixture
- life test
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Abstract
The utility model discloses a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture, including：Resonance amplification disk mechanism, it with vibratory equipment being connected；Hold assembly, it is arranged at the resonance amplification disk mechanism top, the hold assembly includes the first hold assembly and the second hold assembly, first hold assembly is fixedly installed on resonance amplification disk mechanism top, second hold assembly is arranged above the first hold assembly, has the clamp structure coordinated with blade tenon to be measured between the first hold assembly and the second hold assembly.Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture provided by the utility model can provide resonant frequency interior in a big way, it can adapt to high temperature test environment, different blades to be measured is adapted to by replacing hold assembly, therefore the test of a variety of blades to be measured can be applicable in, and the fixture is small, it is light-weight, it is easy to install and use, help significantly to simplify the testing fatigue flow of blade.
Description
Technical field
More particularly to a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture of the utility model, belongs to
In blade of aviation engine experimental technique field.
Background technology
Operating temperature highest described in blade, stress is most complicated, is the mechanism that environment is the most severe on engine, its blade
Quantity is more, complex-shaped, and difficulty of processing is big, and yield rate is relatively low, is manufactured more using high temperature alloy, and the production cost of blade is high,
It is one of core part of engine.The quality of blade fatigue performance, directly affects the life and reliability work of engine.
The function of test fixture is that the movement of shake table and energy are transmitted to test specimen, wishes moving-coil by vibrational energy in experiment
Test specimen is passed to by fixture without distortion.This requires the rigidity of fixture is as big as possible.Due to when fixture resonates, inputting
Identical value will be no longer kept with output, and the kinematic parameter of each point does not keep identical value yet on fixture, it is thus right
Vibration test has an impact.Therefore, industry serious hope always for a long time, which develops one kind, contributes to disc type aero-engine
The fixture that the high-temperature high-frequency fatigue life of blade is accurately tested.
Existing conventional clamp, generally requires and avoids resonating with test specimen to be measured, and simple utilization vibration test equipment, its
The vibration level of offer is relatively low, it is impossible to provides real performance test environment.
Utility model content
The main purpose of the utility model is that provide a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life
Test fixture, with overcome the deficiencies in the prior art.
To realize foregoing purpose of utility model, the technical solution adopted in the utility model includes：
The utility model embodiment provides a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life test clip
Tool, including：Resonance amplification disk mechanism, it is connected with vibrating the moving component of occurrence of equipment；And
Hold assembly, it is fixedly installed on the resonance amplification disk mechanism top, and the hold assembly includes the first folder
Component and the second hold assembly are held, first hold assembly is fixedly installed on the resonance amplification disk mechanism top, described
Second hold assembly is arranged above first hold assembly, is had between first hold assembly and the second hold assembly
The clamp structure coordinated with blade tenon to be measured.
Further, the first hold assembly top is provided with first boss, and the second hold assembly lower part is set
There is second boss, the tongue-and-groove coordinated with blade tenon to be measured is equipped with the first boss and second boss, so that described
The clamp structure is cooperatively formed between first boss and second boss.
Further, the second hold assembly lower part is provided with an at least positive stop lug boss, on first hold assembly
Portion has the groove that is correspondingly arranged with the positive stop lug boss, one end of the positive stop lug boss can engage with the groove.
Further, first hold assembly and the second hold assembly are both provided with threaded hole, first clamping part
Part and the second hold assembly are connected by trip bolt.
Further, the resonance amplification disk mechanism is provided with the threaded hole for connecting the first connecting portion part and answers
Several screw mounting holes to be connected with vibration occurrence of equipment.
Further, a plurality of screw mounting holes are distributed in the edge of the resonance amplification disk mechanism.
In some more specific embodiment, the disc type blade of aviation engine high-temperature high-frequency fatigue life surveys
Examination fixture further includes：The cooling medium channel being continuously arranged in the resonance amplification disk mechanism.
Further, the radial direction that the cooling medium channel amplifies disk mechanism along the resonance runs through the resonance
Amplify disk mechanism, and can be connected with cooling medium circulating mechanism.
Further, the cooling medium circulating mechanism that is provided at both ends with to connect of the cooling medium channel connects
Head.
Preferably, the vibration occurrence of equipment includes electric vibration table.
Compared with prior art, include the advantages of the utility model：Disc type aero-engine provided by the utility model
Blade high-temperature high-frequency fatigue life test fixture, it is simple in structure, resonant frequency interior in a big way can be provided, and can fit
High temperature test environment is answered, different blades to be measured is adapted to by replacing hold assembly, therefore a variety of blades to be measured can be applicable in
Test, and the fixture is small, light-weight, easy to install and use, simplifies the flow of blade fatigue test.
Brief description of the drawings
Fig. 1 is disc type blade of aviation engine high-temperature high-frequency fatigue life survey in one exemplary embodiments of the utility model
Try the structure diagram of fixture；
Fig. 2 is disc type blade of aviation engine high-temperature high-frequency fatigue life survey in one exemplary embodiments of the utility model
Try the front view of fixture；
Fig. 3 is the profile at A-A in Fig. 2；
Description of reference numerals：1- resonance amplification disks, the first hold assemblies of 2-, 21- first boss, 22- grooves, 3- second
Hold assembly, 31- second boss, 32- positive stop lug boss, 4- screws, 5- connectors, 6- cooling medium channels, 7- screw mounting holes, 8-
Clamp structure.
Embodiment
In view of deficiency of the prior art, inventor is able to propose that this practicality is new through studying for a long period of time and largely putting into practice
The technical solution of type.The technical solution, its implementation process and principle etc. will be further explained as follows.
The utility model embodiment provides a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life test clip
Tool, including：Resonance amplification disk mechanism, it is connected with vibrating the moving component of occurrence of equipment；And
Hold assembly, it is fixedly installed on the resonance amplification disk mechanism top, and the hold assembly includes the first folder
Component and the second hold assembly are held, first hold assembly is fixedly installed on the resonance amplification disk mechanism top, described
Second hold assembly is arranged above first hold assembly, is had between first hold assembly and the second hold assembly
The clamp structure coordinated with blade tenon to be measured.
Further, the first hold assembly top is provided with first boss, and the second hold assembly lower part is set
There is second boss, the tongue-and-groove coordinated with blade tenon to be measured is equipped with the first boss and second boss, so that described
The clamp structure is cooperatively formed between first boss and second boss.
Further, the second hold assembly lower part is provided with an at least positive stop lug boss, on first hold assembly
Portion has the groove that is correspondingly arranged with the positive stop lug boss, one end of the positive stop lug boss can engage with the groove.
Further, first hold assembly and the second hold assembly are both provided with threaded hole, first clamping part
Part and the second hold assembly are connected by trip bolt.
Further, the resonance amplification disk mechanism is provided with the threaded hole for connecting the first connecting portion part and answers
Several screw mounting holes to be connected with vibration occurrence of equipment.
Further, a plurality of screw mounting holes are distributed in the edge of the resonance amplification disk mechanism.
In some more specific embodiment, the disc type blade of aviation engine high-temperature high-frequency fatigue life surveys
Examination fixture further includes：The cooling medium channel being continuously arranged in the resonance amplification disk mechanism.
Further, the radial direction that the cooling medium channel amplifies disk mechanism along the resonance runs through the resonance
Amplify disk mechanism, and can be connected with cooling medium circulating mechanism.
Further, the cooling medium circulating mechanism that is provided at both ends with to connect of the cooling medium channel connects
Head.
Preferably, the vibration occurrence of equipment includes electric vibration table.
The technical solution, its implementation process and principle etc. will be further explained with reference to attached drawing as follows.
Referring to Fig. 1, a kind of disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture, including：Resonance
Amplify disk 1, have a plurality of screw mounting holes 7, the middle area of resonance amplification disk 1 along the edge distribution of resonance amplification disk 1
Domain is provided with threaded hole (not shown), and screw mounting hole 7 can coordinate with attachment screw by resonance amplification disk 1 and vibration
Equipment connects,
Hold assembly, is arranged at 1 top of resonance amplification disk, and hold assembly includes the first hold assembly 2 and the second clamping
Component 3, the first hold assembly 2 are fixedly installed on 1 top of resonance amplification disk by attachment screw, and the second hold assembly 3 is set
Above the first hold assembly 2, threaded hole, the first clamping part are both provided with the first hold assembly 2 and the second hold assembly 3
2 and second hold assembly 3 of part is connected by trip bolt 4, between the first hold assembly 2 and the second hold assembly 3 have with
The clamp structure 8 that blade tenon to be measured coordinates.
Referring to Fig. 3, being provided with first boss 21 on the top of the first hold assembly 2, the lower part of the second hold assembly 3 is set
Second boss 31 is equipped with, 31 are respectively provided with the tongue-and-groove coordinated with blade tenon to be measured on 21 and second platform of first boss, and first is convex
Platform 21 and second boss 31 cooperatively form the clamping device 8 for clamping blade.
In some more specific embodiment, the lower part of the second hold assembly 3 is provided with positive stop lug boss 31, limit convex
One end of platform has a lug boss, on the top of the first hold assembly there is the lug boss with 1 one end of positive stop lug boss to be correspondingly arranged
Groove 22, the lug boss of positive stop lug boss one end can engage with groove 22, to play spacing effect.
In other more specific embodiment, also continuously it is provided with cooling in the inside of resonance amplification disk 1 and is situated between
Matter passage 6, cooling medium channel 6 amplify disk along the radial direction of resonance amplification disk 1 through the resonance, and by cold
But the connector 5 that medium channel both ends are set is connected with cooling medium circulating mechanism, to prevent its temperature mistake in the operating condition
Normal work that is high and influencing fixture and service life.
It is high using disc type blade of aviation engine provided by the utility model in some more specific embodiment
When warm high-cycle fatigue life test fixture carries out testing experiment, the first hold assembly is fixedly mounted on electric vibration table, is unclamped
Trip bolt 4, separates the first hold assembly and the second hold assembly, and the tenon of blade to be measured is installed on the first clamping part
In the tongue-and-groove of part first boss, trip bolt is then tightened, the tongue-and-groove of the second hold assembly second boss is covered on blade
On tenon, the tongue-and-groove on the tongue-and-groove and second boss in first boss forms the clamp structure of installation blade tenon, by adjusting
Then trip bolt starts electric vibration table, starts blade fatigue test, in vibration processes to adapt to different blade tenons
In, when blade uses sensing heating, fixture can also be in induction zone, can be heated together with blade, fixture long-time high temperature shakes
It is visibly moved fragile, and its resonant frequency can be reduced gradually, influence to test, and be in addition protection shake table, it is necessary to reduce heat and pass to
On vibratory equipment, the cooling medium in its internal cooling medium channel set can make the temperature of resonance amplification beam will not mistake
Height, so as to improve its service life and measuring accuracy.
When carrying out the blade testing of different size again, it can adjust on the first hold assembly and the second hold assembly boss
Tongue-and-groove shape either structure or is only needed to change with blade to be measured matched hold assembly is thought, so as to improve fixture
Utilization rate, reduces the cost of test, the unnecessary waste also avoided.
Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture provided by the utility model, structure letter
It is single, resonant frequency interior in a big way can be provided, and high temperature test environment is can adapt to, fitted by replacing hold assembly
Different blades to be measured is answered, therefore the test of a variety of blades to be measured can be applicable in, and the fixture is small, light-weight, peace
Fill and easy to use, simplify the flow of blade fatigue test.
It should be appreciated that above-described embodiment is only the technical concepts and features for illustrating the utility model, it is ripe its object is to allow
The content of the utility model can be understood and implement according to this by knowing the personage of technique, can not limit the utility model with this
Protection domain.All equivalent change or modifications made according to the utility model Spirit Essence, should all cover in the utility model
Within protection domain.
Claims (10)
- A kind of 1. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture, it is characterised in that including：Resonance amplification disk mechanism, it is connected with vibrating the moving component of occurrence of equipment；AndHold assembly, it is fixedly installed on the resonance amplification disk mechanism top, and the hold assembly includes the first clamping part Part and the second hold assembly, first hold assembly are fixedly installed on described resonate and amplify disk mechanism top, and described second Hold assembly is arranged above first hold assembly, is had between first hold assembly and the second hold assembly with treating Survey the clamp structure that blade tenon coordinates.
- 2. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1, its feature exists In：The first hold assembly top is provided with first boss, and the second hold assembly lower part is provided with second boss, described The tongue-and-groove coordinated with blade tenon to be measured is equipped with first boss and second boss, so that the first boss and second convex The clamp structure is cooperatively formed between platform.
- 3. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1 or claim 2, its feature It is：The second hold assembly lower part is provided with an at least positive stop lug boss, the first hold assembly top have with it is described The groove that positive stop lug boss is correspondingly arranged, one end of the positive stop lug boss can engage with the groove.
- 4. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1 or claim 2, its feature It is：First hold assembly and the second hold assembly are both provided with threaded hole, first hold assembly and the second clamping Component is connected by trip bolt.
- 5. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1, its feature exists In：The resonance amplification disk mechanism be provided with threaded hole for connecting the first connecting portion part and it is a plurality of to vibration The screw mounting hole of occurrence of equipment connection.
- 6. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 5, its feature exists In：A plurality of screw mounting holes are distributed in the edge of the resonance amplification disk mechanism.
- 7. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1, its feature exists In further including：The cooling medium channel being continuously arranged in the resonance amplification disk mechanism.
- 8. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 7, its feature exists In：The radial direction that the cooling medium channel amplifies disk mechanism along the resonance amplifies disk mechanism through the resonance, And it can be connected with cooling medium circulating mechanism.
- 9. according to the disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture of claim 7 or 8, its feature It is：The connector for being provided at both ends with to connect cooling medium circulating mechanism of the cooling medium channel.
- 10. disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture according to claim 1, its feature exists In：The vibration occurrence of equipment includes electric vibration table.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721315180.8U CN207358923U (en) | 2017-10-12 | 2017-10-12 | Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721315180.8U CN207358923U (en) | 2017-10-12 | 2017-10-12 | Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture |
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| Publication Number | Publication Date |
|---|---|
| CN207358923U true CN207358923U (en) | 2018-05-15 |
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ID=62347310
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721315180.8U Active CN207358923U (en) | 2017-10-12 | 2017-10-12 | Disc type blade of aviation engine high-temperature high-frequency fatigue life test fixture |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108918070A (en) * | 2018-08-28 | 2018-11-30 | 苏州长菱测试技术有限公司 | A kind of vibration fatigue test device for high frequency stress blade |
| 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 |
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | A kind of air-cooling apparatus for high-temperature vibrating test |
| CN114235319A (en) * | 2021-12-15 | 2022-03-25 | 中国航发动力股份有限公司 | Hollow turbine blade testing device and method |
-
2017
- 2017-10-12 CN CN201721315180.8U patent/CN207358923U/en active Active
Cited By (5)
| 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 |
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | A kind of air-cooling apparatus for high-temperature vibrating test |
| CN108918070A (en) * | 2018-08-28 | 2018-11-30 | 苏州长菱测试技术有限公司 | A kind of vibration fatigue test device for high frequency stress blade |
| CN114235319A (en) * | 2021-12-15 | 2022-03-25 | 中国航发动力股份有限公司 | Hollow turbine blade testing device and method |
| CN114235319B (en) * | 2021-12-15 | 2024-03-19 | 中国航发动力股份有限公司 | Hollow turbine blade test device and method |
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