CN204152933U - Bolt cover - Google Patents
Bolt cover Download PDFInfo
- Publication number
- CN204152933U CN204152933U CN201420475671.9U CN201420475671U CN204152933U CN 204152933 U CN204152933 U CN 204152933U CN 201420475671 U CN201420475671 U CN 201420475671U CN 204152933 U CN204152933 U CN 204152933U
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- Prior art keywords
- bolt
- cover
- fixing bolt
- state
- limit stoper
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Abstract
The utility model discloses a kind of bolt cover, for covering in airplane engine for by two interconnective parts connecting bolts of parts.This bolt cover is connected to airplane engine via cover fixing bolt and is provided with for operationally carrying out spacing limit stoper to cover fixing bolt further, limit stoper is operationally in the first state and the second state, when limit stoper is in the first state, can operate cover fixing bolt, and when limit stoper is in the second state, cover fixing bolt is limited and can not come off.Bolt cover of the present utility model can reduce the possibility that the cover fixing bolt for fixing bolt cover itself comes off, and correspondingly reduces the possibility that parts connecting bolt comes off, and further increases the safety and reliability of motor.
Description
Technical field
The utility model relates to energy and power engineering firing unit field, the bolt cover particularly in airplane engine.
Background technique
In airplane engine, in firing chamber, casing is connected with preposition Diffuser and generally adopts bolt to coordinate the fastening piece of self-locking nut and so on, and this place's fastening piece screw-down torque is large, locking require high, so adopt self-locking nut.Reason is, this adpting flange limit, place next-door neighbour's high pressure drum barrel axle, drum barrel axle is connected to high-pressure compressor and high-pressure turbine, for high-speed rotary turntable, if casing and preposition Diffuser connecting bolt occur to loosen the flange edge that even comes off in firing chamber, to cause great damage to high pressure drum barrel axle, and even rupture, this is great hidden danger to the safety and reliability of motor.
Therefore, ripe commercial engines is all herein outside connecting bolt, and construction bolt cover, to reduce the possibility of bolt falling as far as possible.This kind of bolt cover structure all adopts part connecting bolt clamping bolt cover, then remains the scheme of bolt with bolt cover parcel.These scheme Problems existing are exactly the bolt of this part clamping bolt cover, and due to the needs of assembling, do not covered, itself still exists the possibility come off.
Model utility content
The purpose of this utility model is between two parts of reduction airplane engine, and the possibility that especially in firing chamber, between casing and preposition Diffuser, connecting bolt comes off improves engine health and reliability.
For achieving the above object, the utility model provides a kind of bolt cover, for covering in airplane engine for by two interconnective parts connecting bolts of parts, described bolt cover is connected to described airplane engine via cover fixing bolt, it is characterized in that: described bolt cover is provided with for operationally carrying out spacing limit stoper to described cover fixing bolt further, described limit stoper is operationally in the first state and the second state, when described limit stoper is in the first state, can operate described cover fixing bolt, and when described limit stoper is in the second state, described cover fixing bolt is limited and can not come off.
Preferably, cover fixing bolt is made up of head and screw rod, thus when described limit stoper is in the second state, the top surface of described limit stoper next-door neighbour or the head against described cover fixing bolt.
Preferably, described limit stoper is elastic component, and described elastic component can resiliently deformable thus make it be in described first state and described second state respectively.
In one preferred embodiment, described bolt cover comprises body, shielding part and joint, described shielding part arranges on the body and for hiding described parts connecting bolt, described joint is for being connected to described airplane engine via described cover fixing bolt by described bolt cover.
In above preferred embodiment, described shielding part and described joint can lay respectively at described body both sides, and the position corresponding with described joint of described shielding part is provided with breach, and described breach is convenient to operate described cover fixing bolt.
In above preferred embodiment, described body can be tubular elements, described shielding part is the plate extended radially outward from one end of described tubular elements, described joint is the multiple lugs extended radially outward from the other end of described tubular elements, described lug is provided with attachment hole, and described attachment hole is for installing described cover fixing bolt.
Preferably, described limit stoper be arranged in the middle part of described tubular elements with the spring sheet of described attachment hole corresponding position, described spring sheet can resiliently deformable and be in described first state and described second state respectively.
Preferably, described spring sheet and described body are integrally formed or through being welded to connect to described body.
Preferably, described body, described shielding part and described joint are integrally formed.
Preferably, described two parts be respectively airplane engine firing chamber in casing and preposition Diffuser.
The utility model by carrying out spacing to the bolt of fixing bolt cover, thus reduces the possibility of this part bolt falling, improves engine health and reliability.Meanwhile, the bolt falling possibility of fixing bolt cover reduces, and the corresponding possibility reducing remaining part bolt falling, further increases the safety and reliability of motor.
Accompanying drawing explanation
The partial perspective view of bolt cover when Fig. 1 is first state that is according to an embodiment of the present utility model.
Fig. 2 is the partial perspective view of the bolt cover of Fig. 1 when being in the second state.
Description of reference numerals:
100-bolt cover
1-bolt cover body
2-shielding part
21-breach
3-joint
31-attachment hole
4-cover fixing bolt
41-cover fixing bolt head surface
5-spring sheet
Embodiment
Below with reference to accompanying drawing, preferred embodiment of the present utility model is described in detail, understands the purpose of this utility model, feature and advantage so that clearer.It should be understood that embodiment shown in the drawings is not the restriction to the utility model scope, and the connotation just in order to technical solutions of the utility model are described.In accompanying drawing, the same or analogous reference character of identical element indicates.
Relational language and explanation thereof:
Firing chamber: in combustion gas wheel, for organizing the parts of fuel generation combustion reaction;
Casing: the housing being included in outside, firing chamber, for the formation of the framework of structure and load;
Bolt cover: be wrapped in the housing outside bolt, plays heat insulation, prevents the effects such as bolt falling.
Below in conjunction with accompanying drawing, the utility model is described in more detail.Fig. 1 and 2 illustrates the stereogram of a part for bolt cover 100 of the present utility model.Bolt cover 100 of the present utility model is connected to airplane engine (not shown) via cover fixing bolt 4, for covering for by two parts interconnective parts connecting bolt (not shown) in airplane engine, thus peventing member connecting bolt comes off.In the present embodiment, casing and preposition Diffuser (not shown) in the firing chamber that these two aircraft componentss are respectively airplane engine.
Come off to prevent cover fixing bolt, bolt cover 100 of the present utility model is provided with for operationally carrying out spacing limit stoper to cover fixing bolt 4 further, this limit stoper is operationally in the first state and the second state, when described limit stoper is in the first state, can operate described cover fixing bolt, and when described limit stoper is in the second state, described cover fixing bolt is limited and can not come off.In the present embodiment, limit stoper is integrated the elastic component (hereafter will further describe) be arranged on bolt cover 100 body.
In the present embodiment, bolt cover 100 is roughly tubular elements, bolt cover 100 comprises body 1, shielding part 2 and joint 3, and shielding part 2 is wholely set on body 1 and for masking material connecting bolt, joint 3 is for being connected to airplane engine via cover fixing bolt 4 by bolt cover 100.
Body 1, shielding part 2 and joint 3 are integrally formed.(not shown) in other embodiment, body, shielding part 2 and joint 3 also can be independent parts, and are interconnected via modes such as welding.
Shielding part 2 and joint 3 lay respectively at body 1 both sides, and the position corresponding with joint 3 of shielding part 2 is provided with breach 21, and breach 21 is for providing operating space for carrying out operation to cover fixing bolt.The quantity of breach 21 is identical with the quantity of cover fixing bolt, and its size is arranged for ease of instrument and passes to operate cover fixing bolt.
Body 1 is tubular elements (or roughly ring-shaped article), shielding part 1 is the plate extended radially outward from one end of tubular elements, joint 3 is the multiple lugs extended radially outward from the other end of tubular elements, lug is provided with attachment hole 31, attachment hole 31 is for passing for cover fixing bolt 4, with mounting cup fixing bolt 4.
In the middle part of tubular elements, be provided with spring sheet 5 with attachment hole 31 corresponding position, this spring sheet 5 resiliently deformable and being in respectively can not affect the first state operated cover fixing bolt 4 and the second state limited cover fixing bolt.Cover fixing bolt is made up of head and screw rod, in the second state, spring sheet adjacent to or the top surface of head against cover fixing bolt 4.That is, spring sheet 5 can be positioned to cylinder interior location, as shown in Figure 1, and now can assembling-disassembling bolt cover.Or spring sheet is also positioned at and can, to cylinder outer position, as shown in Figure 2, now can carries out spacing to cover fixing bolt 4.
Preferably, spring sheet 5 and body 1 are integrally formed.Preferably, spring sheet can directly on the body 1 of bolt cover metal plate punching shaping.
Or spring sheet also can through being welded to connect to body 1.
The material of bolt cover can be selected according to specific works environment, can adopt stainless steel or refractory alloy.
In bolt cover of the present utility model, by arranging the limit stoper that can be in two states, can carry out spacing to cover fixing bolt, prevent it from coming off, not hindering that again cover fixing bolt is operated.
Bolt cover of the present utility model has following beneficial effect:
1. reduce the possibility of the bolt falling being used for fixing bolt cover itself, improve engine health and reliability;
2. the bolt falling possibility of fixing bolt cover reduces, and the corresponding possibility reducing remaining part bolt falling, further increases the safety and reliability of motor.
It is pointed out that the bolt cover of this structural type not only can be used on combustion box and connects, also can be used for morely on the engine turning stationary fit region, such as, for turbine part.
Below described preferred embodiment of the present utility model in detail, but it will be appreciated that, after having read above-mentioned instruction content of the present utility model, those skilled in the art can make various changes or modifications the utility model.These equivalent form of values fall within the application's appended claims limited range equally.
Claims (10)
1. a bolt cover, for covering in airplane engine for by two interconnective parts connecting bolts of parts, described bolt cover is connected to described airplane engine via cover fixing bolt, it is characterized in that: described bolt cover is provided with for operationally carrying out spacing limit stoper to described cover fixing bolt further, described limit stoper is operationally in the first state and the second state, when described limit stoper is in the first state, can operate described cover fixing bolt, and when described limit stoper is in the second state, described cover fixing bolt is limited and can not come off.
2. bolt cover according to claim 1, is characterized in that: described cover fixing bolt is made up of head and screw rod, when described limit stoper is in the second state, and the top surface of described limit stoper next-door neighbour or the head against described cover fixing bolt.
3. bolt cover according to claim 1, is characterized in that: described limit stoper is elastic component, and described elastic component can resiliently deformable thus make it be in described first state and described second state respectively.
4. bolt cover according to claim 1, it is characterized in that: described bolt cover comprises body, shielding part and joint, described shielding part arranges on the body and for hiding described parts connecting bolt, described joint is for being connected to described airplane engine via described cover fixing bolt by described bolt cover.
5. bolt cover according to claim 4, it is characterized in that: described shielding part and described joint lay respectively at described body both sides, and the position corresponding with described joint of described shielding part is provided with breach, described breach is convenient to operate described cover fixing bolt.
6. bolt cover according to claim 5, it is characterized in that: described body is tubular elements, described shielding part is the plate extended radially outward from one end of described tubular elements, described joint is the multiple lugs extended radially outward from the other end of described tubular elements, described lug is provided with attachment hole, and described attachment hole is for installing described cover fixing bolt.
7. bolt cover according to claim 5, it is characterized in that: described limit stoper be arranged in the middle part of described tubular elements with the spring sheet of described attachment hole corresponding position, described spring sheet can resiliently deformable and be in described first state and described second state respectively.
8. bolt cover according to claim 7, is characterized in that: described spring sheet be integrally formed with described body or through welding, cutting ferrule is connected to described body.
9. bolt cover according to claim 4, is characterized in that: described body, described shielding part and described joint are integrally formed.
10. bolt cover according to claim 1, is characterized in that: casing and preposition Diffuser in the firing chamber that described two parts are respectively airplane engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420475671.9U CN204152933U (en) | 2014-08-22 | 2014-08-22 | Bolt cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420475671.9U CN204152933U (en) | 2014-08-22 | 2014-08-22 | Bolt cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204152933U true CN204152933U (en) | 2015-02-11 |
Family
ID=52511053
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420475671.9U Active CN204152933U (en) | 2014-08-22 | 2014-08-22 | Bolt cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204152933U (en) |
-
2014
- 2014-08-22 CN CN201420475671.9U patent/CN204152933U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP01 | Change in the name or title of a patent holder |