CN203628049U - Metal bushing for aero-engine guide tube - Google Patents
Metal bushing for aero-engine guide tube Download PDFInfo
- Publication number
- CN203628049U CN203628049U CN201320876187.2U CN201320876187U CN203628049U CN 203628049 U CN203628049 U CN 203628049U CN 201320876187 U CN201320876187 U CN 201320876187U CN 203628049 U CN203628049 U CN 203628049U
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- CN
- China
- Prior art keywords
- lining
- metal
- aero
- bushing
- guide tube
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- Expired - Fee Related
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Abstract
The utility model discloses a metal bushing for an aero-engine guide tube, wherein at present, an aero-engine high-temperature guide tube is mainly supported and fixed by means of a clamp and a copper bushing, and the structure is low in use temperature and bad in damping effect; however, with the increasing of the thrust of an aero-engine, higher requirements are put forward on the temperature resistance and damping performance of a support point, and the existing structure is already incapable of meeting the use requirements. The utility model discloses a metal bushing for an aero-engine guide tube. The metal bushing comprises a bushing straight-tube section and bushing flangings at the both sides, and the bushing straight-tube section is provided with a bushing straight-tube section elastic opening; the metal bushing is installed on the aero-engine guide tube, externally clamped by a clamp, and fixedly installed on an engine; the metal bushing is used as a pad and cooperated with the clamp to support and fix the aero-engine guide tube, thus playing the roles of damping and protecting the guide tube from being damaged by the clamp and worn.
Description
Technical field
The present invention relates to the metal lining that a kind of aircraft engine duct is used, the lining of high temperature resistant, the high damping property that refers more particularly to that a kind of aircraft engine duct uses.
Background technique
At present, aeroengine high temperature conduit mainly adopts the mode of clip+copper bush support and fix, and this structure serviceability temperature is low, and damping effect is poor.But along with the increase of aeroengine thrust, strong point temperature tolerance and damping property are had higher requirement, existing structure can not meet usage requirement.
Summary of the invention
The object of the invention is, for solving above-mentioned deficiency, to meet the requirement of High Performance Aeroengine to temperature tolerance and damping property, and design a kind of metal lining that aeroengine high temperature conduit uses that meets.
The technical problem solving
The present invention need to solve the temperature tolerance and the damping property that had both guaranteed lining, considers again manufacturability and the Economy of lining, can meet the matching requirements of aeroengine simultaneously.
Technological scheme
In order to solve the problems of the technologies described above, the present invention is achieved through the following technical solutions:
The metal lining that aircraft engine duct is used comprises lining straight length and a both sides lining flange, is provided with a lining straight length elastic opening at lining straight length.Metal lining is mounted on aircraft engine duct, and clip banding is used in outside, is fixedly mounted on motor.Metal lining, as mat, supports and stationary engine conduit with clip is supporting, plays the effect that damping and protection engine duct are not crushed, wear and tear by clip.
Described metal lining is the mat of selecting a kind of metal wire knitted of stainless steel material, and integral die becomes the fitting surface shape of engine duct and clip.The lining flow development length of metal lining is 12 millimeters, both sides lining flange thickness is 2 millimeters, and at lining internal diameter, during from 6-60 millimeter scope, the wall thickness of selecting lining straight length is 2-3 millimeter, the height of both sides lining flange is 4.5-5.5 millimeter, and lining straight length elastic opening is 2-4.5 millimeter.
Compared with prior art, the invention has the beneficial effects as follows:
1. the serviceability temperature of stainless steel material can get at more than 400 ℃, is much better than copper (T2), can meet the development need of aeroengine.
2. the mat of wire establishment is with reference to shock absorption principles such as honeycombs, and damping property is better than the lining that existing copper sheet is made.
3. design the lining with flange according to the fitting surface shape of conduit and clip, do not needed lining riveted joint or be welded on clip, be easy to processing and assembling.
Accompanying drawing explanation
Fig. 1 metal lining structural drawing,
The side view that 1-metal lining 2-lining flange 3-lining flange thickness 4-lining straight length 5-lining internal diameter Fig. 2 is metal lining
6-lining straight length elastic opening
Fig. 3 is that metal lining is arranged on schematic diagram on conduit
7-engine duct 8-clip
Fig. 4 is that the A of Fig. 3 is to view
Embodiment
Below by embodiment, the present invention is further described.It is descriptive below implementing, and is not determinate, can not limit protection scope of the present invention with this.
The metal lining 1 of being used by the known a kind of aircraft engine duct of Fig. 1, Fig. 2, Fig. 3 and Fig. 4 comprises lining straight length 4 and both sides lining flange 2, is provided with a lining straight length elastic opening 6 at lining straight length 4.Metal lining 1 is mounted on aircraft engine duct 7, outside with clip 8 bandings, is fixedly mounted on motor.Metal lining 1, as mat, supports and stationary engine conduit 7 with clip 8 is supporting, plays the effect that damping and protection engine duct 7 are not crushed, wear and tear by clip 8.
Described metal lining 1 is the mat of selecting a kind of metal wire knitted of stainless steel material, and integral die becomes the fitting surface shape of engine duct 7 and clip 8.Lining straight length 4 length of metal lining 1 are 12 millimeters, both sides lining flange thickness 3 is 2 millimeters, in the time that lining internal diameter 5 is 6-60 millimeter scope, the wall thickness of selecting lining straight length 4 is 2-3 millimeter, the height of both sides lining flange 2 is 4.5-5.5 millimeter, and lining straight length elastic opening 6 is 2-4.5 millimeter.
Application example:
When lining straight length 4 length of metal lining 1 are 12 millimeters, both sides lining flange thickness 3 is 2 millimeters, and in the time that lining internal diameter 5 is 6-14 millimeter scope, the wall thickness of selecting lining straight length 4 is 2 millimeters, the height of both sides lining flange 2 is 4.5 millimeters, and lining straight length elastic opening 6 is 2 millimeters; In the time that lining internal diameter 5 is 16-22 millimeter scope, the wall thickness of selecting lining straight length 4 is 2 millimeters, and the height of both sides lining flange 2 is 4.5 millimeters, and lining straight length elastic opening 6 is 3 millimeters; In the time that lining internal diameter is 25 millimeters, the wall thickness of selecting lining straight length 4 is 3 millimeters, and the height of both sides lining flange 2 is 5.5 millimeters, and lining straight length elastic opening 6 is 4 millimeters; In the time that lining internal diameter 5 is 32-60 millimeter scope, the wall thickness of selecting lining straight length is 3 millimeters, and the height of both sides lining flange 2 is 5.5 millimeters, and lining straight length elastic opening is 4.5 millimeters.
Claims (3)
1. the metal lining that aircraft engine duct is used, it is upper that metal lining (1) is mounted in aircraft engine duct (7), outside with clip (8) banding, is fixedly mounted on motor; It is characterized in that: metal lining (1), as mat, supports and stationary engine conduit (7) with clip (8) is supporting; Metal lining (1) comprises lining straight length (4) and both sides lining flange (2), is provided with a lining straight length elastic opening (6) at lining straight length (4).
2. the metal lining that a kind of aircraft engine duct according to claim 1 is used, it is characterized in that: metal lining (1) is the mat of selecting a kind of metal wire knitted of stainless steel material, integral die becomes the fitting surface shape of engine duct (7) and clip (8).
3. the metal lining that a kind of aircraft engine duct according to claim 1 is used, it is characterized in that: lining straight length (4) length of metal lining (1) is 12 millimeters, both sides lining flange thickness (3) are 2 millimeters, in the time that lining internal diameter (5) is 6-60 millimeter scope, the wall thickness of selecting lining straight length (4) is 2-3 millimeter, the height of both sides lining flange (2) is 4.5-5.5 millimeter, and lining straight length elastic opening (6) is 2-4.5 millimeter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320876187.2U CN203628049U (en) | 2013-12-24 | 2013-12-24 | Metal bushing for aero-engine guide tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320876187.2U CN203628049U (en) | 2013-12-24 | 2013-12-24 | Metal bushing for aero-engine guide tube |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203628049U true CN203628049U (en) | 2014-06-04 |
Family
ID=50814526
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320876187.2U Expired - Fee Related CN203628049U (en) | 2013-12-24 | 2013-12-24 | Metal bushing for aero-engine guide tube |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203628049U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042193A (en) * | 2015-07-15 | 2015-11-11 | 中国船舶重工集团公司第七一九研究所 | Vibration isolation device for high-temperature pipeline |
| CN106594278A (en) * | 2016-11-30 | 2017-04-26 | 河北华北柴油机有限责任公司 | High-pressure oil pipe testing clamp sealing pad |
-
2013
- 2013-12-24 CN CN201320876187.2U patent/CN203628049U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042193A (en) * | 2015-07-15 | 2015-11-11 | 中国船舶重工集团公司第七一九研究所 | Vibration isolation device for high-temperature pipeline |
| CN105042193B (en) * | 2015-07-15 | 2017-03-01 | 中国船舶重工集团公司第七一九研究所 | Isolation mounting for high-temperature pipe |
| CN106594278A (en) * | 2016-11-30 | 2017-04-26 | 河北华北柴油机有限责任公司 | High-pressure oil pipe testing clamp sealing pad |
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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: 20140604 Termination date: 20181224 |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| DD01 | Delivery of document by public notice |
Addressee: Rao Yanglong Document name: Notification of Termination of Patent Right |
|
| DD01 | Delivery of document by public notice |