CN207019856U - One kind is used for engine vane fatigue experimental rig - Google Patents
One kind is used for engine vane fatigue experimental rig Download PDFInfo
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- CN207019856U CN207019856U CN201720718694.1U CN201720718694U CN207019856U CN 207019856 U CN207019856 U CN 207019856U CN 201720718694 U CN201720718694 U CN 201720718694U CN 207019856 U CN207019856 U CN 207019856U
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Abstract
One kind is used for engine vane fatigue experimental rig, including taper pedestal and position clamping and fixing device in the inner, and the taper pedestal is installed on a vibration table by the bolt hole of bottom.It can realize that engine vane fatigue is tested, simulate but be not limited to the detection of engine vane fatigue performance.The device takes into full account that engine blade is smaller and irregular, and the characteristics of being not easy to apply fatigue load, by vibrating the intrinsic frequency of Turbine Blade, the loading of fatigue condition is realized in resonance process, and simple in construction, sole mass is light, convenient operation, securely and reliably.
Description
Technical field
Fatigue test technology field is the utility model is related to, it is more particularly to a kind of to be used for engine vane fatigue experiment dress
Put.
Background technology
Blade is as one of the key of engine and important component, for the structural intergrity and use reliability of engine
With vital effect, the failure of usual blade will cause serious accident, or even fatal crass.So to protect
Demonstrate,prove the safe to use of blade, it is necessary to which its predetermined safe cycle life for examining position is provided by experiment.But due to suffered by blade
Load is more complicated, centrifugal force low circulation load is not only born in engine real work, but also can bear high frequency vibrating
Dynamic loading.Simulation is only capable of under the experiment condition of existing experimental rig and provides centrifugal force low circulation load, high frequency can not be simulated
Load so that trystate is inconsistent with actual working state, and the pre- safe cycle life confidence level for causing experiment to provide is not high,
Hidden danger safe to use be present.Also some experimental rigs are complicated, and vibration transitivity is bad, and own wt is big, for solid
There is the higher blade of frequency to evoke resonance, fatigue loading can not be realized.
The content of the invention
To solve above-mentioned technical problem, the utility model provides a kind of engine vane fatigue that is used for and tests dress
Put, using pyramidal structure, beneficial in the transitive set of vibration, and itself is aircraft aluminum using 7, therefore own wt is light, for compared with
The blade of high natural frequency can also carry out the fatigue loading of big condition.
To achieve the above objectives, the utility model uses following technical scheme：One kind is used for engine vane fatigue and tested
Device, including taper pedestal and position clamping and fixing device in the inner, the bolt hole that the taper pedestal passes through bottom is installed
On a vibration table.
Furtherly, the taper pedestal middle part opens up a through hole a；Taper pedestal in through hole a vertical direction
Two blind holes of different sizes are opened up respectively at left and right sides of middle part, are open big for hole b, are open small for hole c；The taper
Pedestal top center opens up the through hole d of an intercommunicating pore b.
Furtherly, the screwed hole of two connections is provided between hole b and hole c.
Furtherly, the clamping and fixing device includes blade folder, gripping block, bolt push rod and pretension bolt, the leaf
Piece folder is arranged on the inside of taper pedestal by hole b, and in Contraband shape, openend is provided with symmetrical teeth, leaf to be detected in both sides up and down
Piece is arranged in teeth；The gripping block is arranged on the rear side of blade, and blade folder is internal, is pushed away by the bolt in the c of hole
Bar is pressed on blade；The pretension bolt withstands on the top of blade folder by being threadably mounted in the through hole d at the top of taper pedestal
Portion.
Furtherly, the screw putter is threadedly coupled with taper pedestal by the screwed hole between hole b and hole c.
Furtherly, the blade presss from both sides not opening side, and provided with two through holes, bolt push rod is pressed in gripping block through through hole
Left side.
In use, taper pedestal is fixed by bolts on shake table, vibration transmission is carried out；Blade is pressed from both sides and pacified by hole b
Taper base interior is attached to, blade is installed in the teeth of blade folder, gripping block is placed on rear side of blade, by installed in hole
Gripping block is pressed on blade by the bolt push rod in c, and vane simulated blade is held out against in the presence of pretightning force and is rotated in engine
During suffered centrifugal force；Pretension bolt is pressed in the top of blade folder by the through hole d at the top of taper pedestal, in pretightning force
Blade folder is fully clamped blade under effect and carry out fatigue test, opening shake table can be tested.
Compared with prior art, the beneficial effects of the utility model are：The device can realize that engine vane fatigue tries
Test, simulate but be not limited to the detection of engine vane fatigue performance.The device takes into full account that engine blade is smaller and irregular,
The characteristics of being not easy to apply fatigue load, by vibrating the intrinsic frequency of Turbine Blade, realizes fatigue condition in resonance process
Loading, simple in construction, sole mass is light, convenient operation, securely and reliably.
Brief description of the drawings
, below will be to implementing in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
The required accompanying drawing used is briefly described in example or description of the prior art, it should be apparent that, drawings in the following description
It is some embodiments of the utility model, to those skilled in the art, on the premise of creative work of not staying alone, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 is structural representation of the present utility model；
Fig. 2 is half sectional view of the present utility model；
Fig. 3 is the structural representation of taper pedestal of the present utility model；
Fig. 4 is the structural representation of clamping and fixing device of the present utility model.
Wherein, taper pedestal 1, blade folder 2, gripping block 3, bolt push rod 4, pretension bolt 5, teeth 6, hole a, hole b, hole c,
Hole d.
Embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the embodiment of the utility model is clearly and completely described, it is clear that is retouched
The embodiment stated is the utility model part of the embodiment, rather than whole embodiments.Based on the implementation in the utility model
Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, is belonged to
The scope of the utility model protection.
Embodiment 1：
As shown in the figure：One kind is used for engine vane fatigue experimental rig, including taper pedestal 1 and position folder in the inner
Fixing device is held, the taper pedestal 1 is installed on a vibration table by the bolt hole of bottom.
The middle part of taper pedestal 1 opens up a through hole a；The pars intermedia of taper pedestal 1 in through hole a vertical direction
The position left and right sides opens up two blind holes of different sizes respectively, is open big for hole b, is open small for hole c；The taper pedestal 1
Top center opens up the through hole d of an intercommunicating pore b.
The screwed hole of two connections is provided between hole b and hole c.
The clamping and fixing device includes blade folder 2, gripping block 3, bolt push rod 4 and pretension bolt 5, the blade folder 2
The inside of taper pedestal 1 is arranged on from hole b, in Contraband shape, both sides are provided with symmetrical teeth 6, blade peace to be detected up and down for openend
In teeth 6；The gripping block 3 is arranged on the rear side of blade, and blade is pressed from both sides inside 2, pushed away by the bolt in the c of hole
Bar 4 is pressed on blade；The pretension bolt 5 withstands on blade folder 2 by being threadably mounted in the through hole d at the top of taper pedestal 1
Top.
The screw putter 4 is threadedly coupled with taper pedestal 1 by the screwed hole between hole b and hole c.
The blade presss from both sides 2 not opening sides, and provided with two through holes, bolt push rod 4 is pressed in the left side of gripping block 3 through through hole.
In use, taper pedestal 1 is fixed by bolts on shake table, vibration transmission is carried out；Blade folder 2 is passed through into hole b
It is installed to inside taper pedestal 1, blade is installed in the teeth 6 of blade folder 2, gripping block 3 is placed on rear side of blade, passed through
Gripping block 3 is pressed on blade by the bolt push rod 4 in the c of hole, and vane simulated blade is held out against in the presence of pretightning force and is existed
Suffered centrifugal force in engine rotary course；Pretension bolt 5 is pressed in blade folder 2 by the through hole d at the top of taper pedestal 1
Top, blade folder 2 is fully clamped blade in the presence of pretightning force and carry out fatigue test, opening shake table can be carried out
Experiment.
Finally it should be noted that：Above example is only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：
It can still modify to the technical scheme described in foregoing embodiments, or which part technical characteristic is carried out etc.
With replacement；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model technology
The spirit and scope of scheme.
Claims (5)
1. one kind is used for engine vane fatigue experimental rig, it is characterised in that：Including folder taper pedestal and position in the inner
Fixing device is held, the taper pedestal is installed on a vibration table by the bolt hole of bottom；
The clamping and fixing device includes blade folder, gripping block, bolt push rod and pretension bolt,
The blade folder is arranged on the inside of taper pedestal by hole b, and in Contraband shape, openend is provided with symmetrical tooth in both sides up and down
Tooth, blade to be detected are arranged in teeth；
The gripping block is arranged on the rear side of blade, and blade folder is internal, and blade is pressed in by the bolt push rod in the c of hole
On；
The pretension bolt withstands on the top of blade folder by being threadably mounted in the through hole d at the top of taper pedestal.
2. one kind according to claim 1 is used for engine vane fatigue experimental rig, it is characterised in that：The taper base
Seat middle part opens up a through hole a；
Two blind holes of different sizes are opened up at left and right sides of taper pedestal middle part in through hole a vertical direction respectively, are open
It is big for hole b, be open small for hole c；
The taper pedestal top center opens up the through hole d of an intercommunicating pore b.
3. one kind according to claim 2 is used for engine vane fatigue experimental rig, it is characterised in that：Hole b and hole c it
Between be provided with two connection screwed holes.
4. one kind according to claim 1 or 3 is used for engine vane fatigue experimental rig, it is characterised in that：The spiral shell
Line push rod is threadedly coupled with taper pedestal by the screwed hole between hole b and hole c.
5. one kind according to claim 1 is used for engine vane fatigue experimental rig, it is characterised in that：The blade folder
Not opening side, provided with two through holes, bolt push rod is pressed on the left of gripping block through through hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720718694.1U CN207019856U (en) | 2017-06-20 | 2017-06-20 | One kind is used for engine vane fatigue experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720718694.1U CN207019856U (en) | 2017-06-20 | 2017-06-20 | One kind is used for engine vane fatigue experimental rig |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207019856U true CN207019856U (en) | 2018-02-16 |
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ID=61486447
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720718694.1U Active CN207019856U (en) | 2017-06-20 | 2017-06-20 | One kind is used for engine vane fatigue experimental rig |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110006636A (en) * | 2019-03-15 | 2019-07-12 | 南京航空航天大学 | A kind of FOD repeated bend test part and its design method |
| CN111256934A (en) * | 2020-03-31 | 2020-06-09 | 中国航发动力股份有限公司 | Turbine blade vibration test tool and turbine blade clamping method |
| 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 |
| CN114152398A (en) * | 2021-12-02 | 2022-03-08 | 成都市鸿侠科技有限责任公司 | Measuring device and measuring method for natural frequency of aircraft engine 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 |
-
2017
- 2017-06-20 CN CN201720718694.1U patent/CN207019856U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110006636A (en) * | 2019-03-15 | 2019-07-12 | 南京航空航天大学 | A kind of FOD repeated bend test part and its design method |
| CN111256934A (en) * | 2020-03-31 | 2020-06-09 | 中国航发动力股份有限公司 | Turbine blade vibration test tool and turbine blade clamping method |
| 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 |
| CN114152398A (en) * | 2021-12-02 | 2022-03-08 | 成都市鸿侠科技有限责任公司 | Measuring device and measuring method for natural frequency of aircraft engine blade |
| CN114152398B (en) * | 2021-12-02 | 2023-10-27 | 成都市鸿侠科技有限责任公司 | Device and method for measuring natural frequency of aircraft engine 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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