CN207366211U - The high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine - Google Patents
The high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine Download PDFInfo
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- CN207366211U CN207366211U CN201721315177.6U CN201721315177U CN207366211U CN 207366211 U CN207366211 U CN 207366211U CN 201721315177 U CN201721315177 U CN 201721315177U CN 207366211 U CN207366211 U CN 207366211U
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- boss
- resonance
- enlarger
- blade
- fatigue life
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Abstract
The utility model discloses a kind of high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine, including resonance enlarger and clamp assemblies, resonance enlarger lower part is connected through complex root attachment screw with vibrating the moving component of occurrence of equipment, clamp assemblies are fixedly connected with resonance enlarger top, clamp assemblies include first boss and second boss, first boss is arranged on the upper surface of the resonance enlarger, the tongue-and-groove being equipped with blade tenon to be measured is both provided with first boss and second boss, first boss and second boss cooperatively form the clamp structure for clamping blade tenon to be measured.Test fixture provided by the utility model, it is easy to install and use, simplify the flow of blade fatigue test；Fixture provided by the utility model can make fixture and test specimen to be measured resonate, and so as to reach higher vibration level, to approach real working status, and the fixture can adapt to high temperature test environment.
Description
Technical field
The high-temperature high-frequency fatigue life test fixture of more particularly to a kind of clipping blade of aviation engine of the utility model,
Belong to 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.Existing conventional clamp, generally requires and avoids resonating with test specimen to be measured, and examination is vibrated in simple utilizing
Equipment is tested, the vibration level that it is provided 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 high-temperature high-frequency of clipping blade of aviation engine the tired longevity
Test fixture is ordered, 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 high-temperature high-frequency fatigue life test of clipping blade of aviation engine
Fixture, including resonance enlarger and clamp assemblies, the resonance enlarger lower part are sent out through complex root attachment screw and vibration
The moving component connection of generating apparatus, the clamp assemblies are fixedly connected with the resonance enlarger top, the clamp assemblies
Including first boss and second boss, the first boss is arranged on the upper surface of the resonance enlarger, and described first
The tongue-and-groove being equipped with blade tenon to be measured is both provided with boss and second boss, the first boss and second boss are matched somebody with somebody
Close the clamp structure for being formed and being used for clamping blade tenon to be measured.
Preferably, the first boss is wholely set with resonance enlarger.
Further, the clamp assemblies are further included grips part with what resonance enlarger was fixedly connected, and described the
Two boss are fixedly connected with gripping part lower part.
Preferably, the part that grips is fixedly connected with resonance enlarger by attachment screw.
Preferably, the second boss is wholely set with gripping part.
Further, the clamp assemblies further include an at least positive stop lug boss, and the positive stop lug boss is with gripping under part
Portion is fixedly connected, and the resonance enlarger top has a groove coordinated with the positive stop lug boss, and the one of the positive stop lug boss
End can engage with the groove.
Further, one end of the positive stop lug boss have with the groove coordinate protrusion, the positive stop lug boss with
Part is gripped to be wholely set.
Further, the resonance enlarger is resonance amplification beam.
Further, it is additionally provided with cooling medium channel inside the resonance enlarger.
Further, the cooling medium channel is put along the axially consecutive of the resonance enlarger through the resonance
Great institutions, and can be connected with cooling medium circulating apparatus.
Further, the cooling medium channel is provided at both ends with least being connected with cooling medium circulating apparatus
Connector.
Compared with prior art, include the advantages of the utility model：Integral type aero-engine provided by the utility model
The high-temperature high-frequency fatigue life test fixture of blade, it is simple in structure, it is small, it is light-weight, it is easy to install and use, simplify leaf
The flow of piece testing fatigue；In addition, fixture provided by the utility model can make fixture and test specimen to be measured resonate, so as to up to
To higher vibration level, to approach real working status, and the fixture can adapt to high temperature test environment.
Brief description of the drawings
Fig. 1 is the high-temperature high-frequency fatigue life of clipping blade of aviation engine in one exemplary embodiments of the utility model
The structure diagram of test fixture；
Fig. 2 is the high-temperature high-frequency fatigue life of clipping blade of aviation engine in one exemplary embodiments of the utility model
The front view of test fixture；
Fig. 3 is vertical at the B-B of the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine shown in Fig. 2
Section structure diagram；
Fig. 4 is the vertical section structure diagram at C-C in Fig. 3；
Description of reference numerals：1- resonance amplification beams, 2- screws, 3- grip part, 4- connectors, 5- screws, 6- cooling Jie
Matter passage, 7- clamp structures.
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 high-temperature high-frequency fatigue life test of clipping blade of aviation engine
Fixture, including resonance enlarger and clamp assemblies, the resonance enlarger lower part are sent out through complex root attachment screw and vibration
The moving component connection of generating apparatus, the clamp assemblies are fixedly connected with the resonance enlarger top, the clamp assemblies
Including first boss and second boss, the first boss is arranged on the upper surface of the resonance enlarger, and described first
The tongue-and-groove being equipped with blade tenon to be measured is both provided with boss and second boss, the first boss and second boss are matched somebody with somebody
Close the clamp structure for being formed and being used for clamping blade tenon to be measured.
Preferably, the first boss is wholely set with resonance enlarger.
Further, the clamp assemblies are further included grips part with what resonance enlarger was fixedly connected, and described the
Two boss are fixedly connected with gripping part lower part.
Preferably, the part that grips is fixedly connected with resonance enlarger by attachment screw.
Preferably, the second boss is wholely set with gripping part.
Further, the clamp assemblies further include an at least positive stop lug boss, and the positive stop lug boss is with gripping under part
Portion is fixedly connected, and the resonance enlarger top has a groove coordinated with the positive stop lug boss, and the one of the positive stop lug boss
End can engage with the groove.
Further, one end of the positive stop lug boss have with the groove coordinate protrusion, the positive stop lug boss with
Part is gripped to be wholely set.
Further, the resonance enlarger is resonance amplification beam.
Further, it is additionally provided with cooling medium channel inside the resonance enlarger.
Further, the cooling medium channel is put along the axially consecutive of the resonance enlarger through the resonance
Great institutions, and can be connected with cooling medium circulating apparatus.
Further, the cooling medium channel is provided at both ends with least being connected with cooling medium circulating apparatus
Connector.
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 high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine, including：Altogether
Shake amplification beam 1 (i.e. foregoing resonance enlarger) and clamp assemblies, and resonance amplification beam 1 can be connected by screw 2 and vibratory equipment
Connecing, clamp assemblies are fixed on resonance amplification beam top, and clamp assemblies include first boss, second boss and grip part 3, the
One boss is arranged on the upper surface of resonance amplification beam, and second boss is arranged at the lower face for gripping part 3, first boss and
The tongue-and-groove being equipped with blade tenon to be measured is both provided with second boss, the first boss and second boss cooperatively form
For clamping the clamp structure 7 of blade tenon to be measured.Grip part 3 to be fixedly connected with resonance amplification beam by screw 5, screw
5 not only can will grip part 3 be fixedly connected on resonance amplification beam 1 upper surface, be also used as regulating part, pass through adjusting
Screw 5 can also be by the clamping of the tenon of blade to be measured and clamp structure 7.
A few positive stop lug boss is also secured in the lower face for gripping part 3, one end of positive stop lug boss has a protrusion, altogether
Amplification beam 1 top that shakes has the groove set with the male cooperation on positive stop lug boss, and the protrusion of one end of positive stop lug boss can block
Together in groove, to prevent clamp assemblies from moving.
It should be noted that first boss can be wholely set with resonance amplification beam, fixed company can also be provided separately again
Connect, gripping part and second boss and positive stop lug boss can also be wholely set, or separately positioned reconnection, this practicality
It is preferably discrete setting in new.Can be used on part is gripped connection by the use of screw 5 as adjusting mechanism, can also be single
Adjusting mechanism is solely set to adjust clamp structure.
Referring to Fig. 2, in some more specific embodiment, also it is continuous through setting inside resonance amplification beam 1
There is cooling medium channel 6,6 both ends of cooling medium channel are connected with the connector at least to be connected with cooling water medium circulating apparatus
4；When the fixture is in running order, often heating fever, in order to ensure the normal work of fixture, can put to resonance
Cooling medium (such as water) is passed through inside crossbeam to reduce the temperature of fixture, extends its service life etc..
Specifically, surveyed using the high-temperature high-frequency fatigue life of clipping blade of aviation engine provided by the utility model
When examination fixture is tested, the amplification beam that will first can resonate is fixed on the moving component of vibration occurrence of equipment, and it is solid to unclamp clamping
Determine the screw on part top, the tenon of blade to be measured is installed in clamp structure, and the protrusion of positive stop lug boss is sticked in resonance
In the groove for amplifying beam, screw is then tightened, the tenon of blade to be measured is tightly fixed in clamp structure, you can be surveyed
Examination.When being tested, cooling device can be connected, during the test, when blade uses sensing heating, fixture can also be located
In induction zone, can be heated together with blade, fixture long-time high-temperature vibrating is easily damaged, and its resonant frequency can be reduced gradually,
Experiment is influenced, is in addition protection shake table, it is necessary to reduce heat and pass on vibratory equipment, its internal cooling medium channel set
Interior cooling medium can make the temperature of resonance amplification beam will not be excessive, so as to improve its service life and measuring accuracy.
, can be convex according to the specification of blade tenon to be measured setting first boss and second when carrying out different blade testings
Tongue-and-groove specification on platform, or first boss and/or second boss are replaced, without replacing a whole set of test fixture, improve survey
The efficiency of examination, also reduces the cost of test.
The high-temperature high-frequency fatigue life test fixture of integral type blade of aviation engine provided by the utility model, structure letter
It is single, it is small, it is light-weight, it is easy to install and use, simplify the flow of blade fatigue test；In addition, the utility model provides
Fixture fixture and test specimen to be measured can be made to resonate, so as to reach higher vibration level, to approach real work shape
State, and the fixture can adapt to high temperature test environment.
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)
1. the high-temperature high-frequency fatigue life test fixture of a kind of clipping blade of aviation engine, it is characterised in that put including resonance
Great institutions and clamp assemblies, moving component of the resonance enlarger lower part through complex root attachment screw with vibration occurrence of equipment
Connection, the clamp assemblies are fixedly connected with the resonance enlarger top, and the clamp assemblies include first boss and the
Two boss, the first boss is arranged on the upper surface of the resonance enlarger, in the first boss and second boss
The tongue-and-groove being equipped with blade tenon to be measured is both provided with, the first boss and second boss are cooperatively formed to be treated for clamping
Survey the clamp structure of blade tenon.
2. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 1, it is special
Sign is：The first boss is wholely set with resonance enlarger.
3. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 1, it is special
Sign is：The clamp assemblies further include the part that grips being fixedly connected with resonance enlarger, the second boss and folder
Fixing piece lower part is held to be fixedly connected.
4. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 3, it is special
Sign is：The second boss is wholely set with gripping part.
5. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 3, it is special
Sign is：The clamp assemblies further include an at least positive stop lug boss, and the positive stop lug boss is fixedly connected with gripping part lower part,
The resonance enlarger top has a groove coordinated with the positive stop lug boss, one end of the positive stop lug boss can engage with
In the groove.
6. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 5, it is special
Sign is：One end of the positive stop lug boss has the protrusion coordinated with the groove, and the positive stop lug boss is with gripping part one
Body is set.
7. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 1, it is special
Sign is：The resonance enlarger is resonance amplification beam.
8. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 1, it is special
Sign is：Cooling medium channel is additionally provided with inside the resonance enlarger.
9. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 8, it is special
Sign is：The cooling medium channel runs through the resonance enlarger, and energy along resonance the axially consecutive of enlarger
It is enough to be connected with cooling medium circulating apparatus.
10. the high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine according to claim 9, it is special
Sign is：The cooling medium channel is provided at both ends with the connector at least to be connected with cooling medium circulating apparatus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721315177.6U CN207366211U (en) | 2017-10-12 | 2017-10-12 | The high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721315177.6U CN207366211U (en) | 2017-10-12 | 2017-10-12 | The high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207366211U true CN207366211U (en) | 2018-05-15 |
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ID=62347345
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721315177.6U Active CN207366211U (en) | 2017-10-12 | 2017-10-12 | The high-temperature high-frequency fatigue life test fixture of clipping blade of aviation engine |
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| Country | Link |
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| CN (1) | CN207366211U (en) |
Cited By (2)
| 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 |
| CN117054229A (en) * | 2023-10-12 | 2023-11-14 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
-
2017
- 2017-10-12 CN CN201721315177.6U patent/CN207366211U/en active Active
Cited By (3)
| 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 |
| CN117054229A (en) * | 2023-10-12 | 2023-11-14 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
| CN117054229B (en) * | 2023-10-12 | 2023-12-19 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
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