CN203584974U - Embedded fastening connection structure used in aero-engine - Google Patents
Embedded fastening connection structure used in aero-engine Download PDFInfo
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- CN203584974U CN203584974U CN201320521600.3U CN201320521600U CN203584974U CN 203584974 U CN203584974 U CN 203584974U CN 201320521600 U CN201320521600 U CN 201320521600U CN 203584974 U CN203584974 U CN 203584974U
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- self
- locking nut
- embedded
- hole
- nut
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Abstract
An embedded fastening connection structure used in an aero-engine is characterized by comprising a bolt, a first part, a second part, a self-locking nut, and a retainer ring, wherein a mounting hole is processed in the connecting place of the second part; an annular slot is processed in the outer side of the hole; the self-locking nut is mounted in the hole of the second part; the retainer ring is mounted in the slot of the second part and has a fixing and positioning effect on the self-locking nut; the first part and the second part are attached and the centers of the holes of the first and second parts are opposite to each other; and the bolt penetrates through the first part and then is fixedly connected with the self-locking nut in the second part. The embedded fastening connection structure has the advantages that the embedded self-locking nut structure is adopted and the self-locking nut is fixed by mounting the elastic retainer ring; the utilization of the self-locking nut can effectively increase the product assembling efficiency and improve the product maintainability; and at the same time, the embedded fastening connection structure employs the embedded nut structure so that the nut can be replaced timely when screw threads are damaged during the usage process and thus the product maintainability is improved while the product use cost is lowered.
Description
Technical field
The utility model relates to linkage structure field, particularly a kind of embedded fastening structure for aeroengine.
Background technique
The development trend of Aeroengine Design is more and more to focus on its usability, maintainability and maintenance, and it is convenient, flexible that parts are focused in disassembly process.
Two of aeroengine use or the mode that is fastenedly connected of a plurality of parts adopt screw connection structure more, be that one end adopts bolt, the other end adopts is with female part or nut, bolt is through the two or more parts that need to connect, with screw-internal thread fit, play the effect that part is fastenedly connected.Be directed to the part that size is thicker, internal thread multi-processing is in part body, and this structure exists following shortcoming: after the internal thread of part in use damages, screw thread cannot be repaired, and part integral body is scrapped, and user cost is higher; This kind of structure do not have auto-lock function more, and bolt is after installation, and lock silk or the locking plates of adopting tighten more, and installation time is long, and maintainability is lower.For above present situation, need a kind of novel embedded fastening structure of design, this structure adopts embedded self-locking nut structure, can effectively improve maintainability and the maintenance of fastening structure.
Model utility content
The purpose of this utility model is that spy provides a kind of embedded fastening structure for aeroengine in order to improve maintainability and the maintenance of fastening structure.
The utility model provides a kind of embedded fastening structure for aeroengine, it is characterized in that: comprise bolt 1, self-locking nut 4, ring washer 5;
The second part 3 is processed with mounting hole in joint, outside, hole processing one annular groove, self-locking nut 4 is arranged in the hole of the second part 3, ring washer 5 is arranged in the second part 3 grooves, play the stationary positioned effect to self-locking nut 4, the first part 2 and the second part 3 laminatings, the hole heart is relative, and bolt 1 passes the first part 2 and is fixedly connected with the self-locking nut 4 in the second part 3.
In the second part 3, be processed with nut mounting hole, outside, hole processing one annular groove.
Described ring washer 5 is hole Steel Cable Baffle Ring, standard GB/T 895.1-86.
Described self-locking nut 4 tops are six prism structures, restriction nut freely rotating in the second part 3 holes, and bottom is cylindrical structural, is convenient to the axial retention effect of 5 pairs of nuts of ring washer.
Self-locking nut 4 is embedded in the second part 3, by being fastenedly connected of bolt 1 and self-locking nut 4, plays the effect that is fixedly connected with the second part 3 to the first part 2.
Advantage of the present utility model:
Embedded fastening structure for aeroengine described in the utility model, adopts embedded self-locking nut structure, by circlip, fixedly self-locking nut are installed.The use of self-locking nut can effectively improve the efficiency of Product Assembly, improves the maintainability of product, and this structure adopts embedded nut structure simultaneously, after screw thread is in use impaired, can change in time nut, improve the maintenance of product, save the user cost of product.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the utility model is described in further detail:
Fig. 1 is the embedded fastening structure schematic diagram for aeroengine.
Embodiment
Embodiment 1
The present embodiment provides a kind of embedded fastening structure for aeroengine, it is characterized in that: comprise bolt 1, self-locking nut 4, ring washer 5;
The second part 3 is processed with mounting hole in joint, outside, hole processing one annular groove, self-locking nut 4 is arranged in the hole of the second part 3, ring washer 5 is arranged in the second part 3 grooves, play the stationary positioned effect to self-locking nut 4, the first part 2 and the second part 3 laminatings, the hole heart is relative, and bolt 1 passes the first part 2 and is fixedly connected with the self-locking nut 4 in the second part 3.
In the second part 3, be processed with nut mounting hole, outside, hole processing one annular groove.
Described ring washer 5 is hole Steel Cable Baffle Ring, standard GB/T 895.1-86.
Described self-locking nut 4 tops are six prism structures, restriction nut freely rotating in the second part 3 holes, and bottom is cylindrical structural, is convenient to the axial retention effect of 5 pairs of nuts of ring washer.
Self-locking nut 4 is embedded in the second part 3, by being fastenedly connected of bolt 1 and self-locking nut 4, plays the effect that is fixedly connected with the second part 3 to the first part 2.
Claims (4)
1. for an embedded fastening structure for aeroengine, it is characterized in that: the described embedded fastening structure for aeroengine, comprises bolt (1), self-locking nut (4), ring washer (5);
The second part (3) is processed with mounting hole in joint, outside, hole processing one annular groove, self-locking nut (4) is arranged in the hole of the second part (3), ring washer (5) is arranged in the second part (3) groove, play the stationary positioned effect to self-locking nut (4), the first part (2) and the second part (3) laminating, the hole heart is relative, and bolt (1) passes the first part (2) and is fixedly connected with the self-locking nut (4) in the second part (3).
2. according to the embedded fastening structure for aeroengine claimed in claim 1, its structure characteristic is: the second part is processed with nut mounting hole in (3), outside, hole processing one annular groove.
3. according to the embedded fastening structure for aeroengine claimed in claim 1, its structure characteristic is: described ring washer (5) is hole Steel Cable Baffle Ring.
4. according to the embedded fastening structure for aeroengine claimed in claim 1, its structure characteristic is: described self-locking nut (4) top is six prism structures, and bottom is cylindrical structural.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320521600.3U CN203584974U (en) | 2013-08-23 | 2013-08-23 | Embedded fastening connection structure used in aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320521600.3U CN203584974U (en) | 2013-08-23 | 2013-08-23 | Embedded fastening connection structure used in aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203584974U true CN203584974U (en) | 2014-05-07 |
Family
ID=50582904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320521600.3U Expired - Fee Related CN203584974U (en) | 2013-08-23 | 2013-08-23 | Embedded fastening connection structure used in aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203584974U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106151244A (en) * | 2015-04-27 | 2016-11-23 | 长城汽车股份有限公司 | Circlip and circlip erecting device |
| CN110700345A (en) * | 2019-11-15 | 2020-01-17 | 中国船舶重工集团公司第十二研究所 | Dredging reamer tooth system |
-
2013
- 2013-08-23 CN CN201320521600.3U patent/CN203584974U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106151244A (en) * | 2015-04-27 | 2016-11-23 | 长城汽车股份有限公司 | Circlip and circlip erecting device |
| CN110700345A (en) * | 2019-11-15 | 2020-01-17 | 中国船舶重工集团公司第十二研究所 | Dredging reamer tooth system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140507 Termination date: 20160823 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |