CN104728523A - Metal lining for guide tube of aero-engine - Google Patents
Metal lining for guide tube of aero-engine Download PDFInfo
- Publication number
- CN104728523A CN104728523A CN201310738390.8A CN201310738390A CN104728523A CN 104728523 A CN104728523 A CN 104728523A CN 201310738390 A CN201310738390 A CN 201310738390A CN 104728523 A CN104728523 A CN 104728523A
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- CN
- China
- Prior art keywords
- lining
- engine
- metal
- aero
- metal lining
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
- F16L3/08—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing
- F16L3/12—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing
- F16L3/123—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing and extending along the attachment surface
- F16L3/1233—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing and extending along the attachment surface the member being of metal, with or without an other layer of other material
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a metal lining for a guide tube of an aero-engine. At present, a high-temperature guide tube of an aero-engine is supported and fixed by a hoop and a copper lining, the using temperature is low, a damping effect is poor, along with increasing of thrust of the aero-engine, requirements on temperature resistance and damping performance of a supporting point are high, and the existing structure cannot meet the using requirements. The metal lining for the guide tube of the aero-engine comprises a lining straight tube section and two side lining turned edges. An elastic opening is formed in the lining straight tube section. The metal lining is arranged on the guide tube of the aero-engine, the outside of the metal lining is hooped tightly by a hoop, and the metal lining is fixedly arranged on the aero-engine. The metal lining which serves as a pad is matched with the hoop and is used for supporting and fixing the guide tube of the aero-engine, a damping effect is achieved, and the guide tube is protected from being crushed by the hoop and abraded.
Description
Technical field
The present invention relates to a kind of metal lining of aircraft engine duct, refer more particularly to a kind of lining of high temperature resistant, high damping property of aircraft engine duct.
Background technique
At present, aeroengine high temperature conduit mainly adopts the mode of clip+copper bush to carry out supporting and fixing, and this structure serviceability temperature is low, and damping effect is poor.But along with the increase of aeroengine thrust, have higher requirement to strong point temperature tolerance and damping property, existing structure can not meet usage requirement.
Summary of the invention
The object of the invention is for solving above-mentioned deficiency, meeting the requirement of High Performance Aeroengine to temperature tolerance and damping property, and designing a kind of metal lining meeting aeroengine high temperature conduit and use.
The technical problem solved
The present invention needs to solve the temperature tolerance and damping property that had both ensured lining, considers manufacturability and the Economy of lining again, 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 of aircraft engine duct 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, and fixed installation on the engine.Metal lining, as mat, supports and stationary engine conduit with clip is supporting, the effect played damping and protect engine duct not crushed by clip, wear and tear.
Described metal lining is the mat of the metal wire knitted selecting a kind 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, when bushing inner diameter is from 6-60 millimeter scope, selects the wall thickness of lining straight length to be 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 DEG C, is much better than copper (T2), can meets the development need of aeroengine.
2. the mat of wire establishment with reference to the shock absorption principles such as honeycomb, and damping property is better than the lining that existing copper sheet is made.
3. be with the lining of flange according to the fitting surface profile design of conduit and clip, do not need lining riveted joint or be welded on clip, being easy to processing and assembling.
Accompanying drawing explanation
Fig. 1 metal lining structural drawing,
1-metal lining 2-lining flange 3-lining flange thickness 4-lining straight length 5-bushing inner diameter
Fig. 2 is the side view of 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 the A direction view of Fig. 3
Embodiment
Below by embodiment, the present invention is further described.Below implement just descriptive, be not determinate, protection scope of the present invention can not be limited with this.
Comprise lining straight length 4 and both sides lining flange 2 by the metal lining 1 of the known a kind of aircraft engine duct of Fig. 1, Fig. 2, Fig. 3 and Fig. 4, be provided with a lining straight length elastic opening 6 at lining straight length 4.Metal lining 1 is mounted on aircraft engine duct 7, and outside with clip 8 banding, fixed installation on the engine.Metal lining 1, as mat, supports and stationary engine conduit 7 with clip 8 is supporting, the effect played damping and protect engine duct 7 not crushed by clip 8, wear and tear.
Described metal lining 1 is the mat of the metal wire knitted selecting a kind 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 is 12 millimeters, both sides lining flange thickness 3 is 2 millimeters, when bushing inner diameter 5 is 6-60 millimeter scope, the wall thickness of lining straight length 4 is selected to be 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 is 12 millimeters, both sides lining flange thickness 3 is 2 millimeters, when bushing inner diameter 5 is 6-14 millimeter scope, selects the wall thickness of lining straight length 4 to be 2 millimeters, the height of both sides lining flange 2 is 4.5 millimeters, and lining straight length elastic opening 6 is 2 millimeters; When bushing inner diameter 5 is 16-22 millimeter scope, select the wall thickness of lining straight length 4 to be 2 millimeters, the height of both sides lining flange 2 is 4.5 millimeters, and lining straight length elastic opening 6 is 3 millimeters; When bushing inner diameter is 25 millimeters, select the wall thickness of lining straight length 4 to be 3 millimeters, the height of both sides lining flange 2 is 5.5 millimeters, and lining straight length elastic opening 6 is 4 millimeters; When bushing inner diameter 5 is 32-60 millimeter scope, select the wall thickness of lining straight length to be 3 millimeters, 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. a metal lining for aircraft engine duct, metal lining (1) is mounted on aircraft engine duct (7), outside clip (8) banding, and fixed installation is on the engine; 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 of a kind of aircraft engine duct according to claim 1, it is characterized in that: metal lining (1) is the mat of the metal wire knitted selecting a kind of stainless steel material, integral die becomes the fitting surface shape of engine duct (7) and clip (8).
3. the metal lining of a kind of aircraft engine duct according to claim 1, 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, when bushing inner diameter (5) is for 6-60 millimeter scope, the wall thickness of lining straight length (4) is selected to be 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 |
|---|---|---|---|
| CN201310738390.8A CN104728523A (en) | 2013-12-24 | 2013-12-24 | Metal lining for guide tube of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310738390.8A CN104728523A (en) | 2013-12-24 | 2013-12-24 | Metal lining for guide tube of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104728523A true CN104728523A (en) | 2015-06-24 |
Family
ID=53452708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310738390.8A Pending CN104728523A (en) | 2013-12-24 | 2013-12-24 | Metal lining for guide tube of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104728523A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110546350A (en) * | 2017-03-23 | 2019-12-06 | 赛峰飞机发动机公司 | Center support with elastic return for an auxiliary conduit |
-
2013
- 2013-12-24 CN CN201310738390.8A patent/CN104728523A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110546350A (en) * | 2017-03-23 | 2019-12-06 | 赛峰飞机发动机公司 | Center support with elastic return for an auxiliary conduit |
| CN110546350B (en) * | 2017-03-23 | 2022-06-17 | 赛峰飞机发动机公司 | Center support with elastic return for an auxiliary conduit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150624 |
|
| WD01 | Invention patent application deemed withdrawn after publication |