CN113983239A - Quick assembly and disassembly clamp for aero-engine - Google Patents
Quick assembly and disassembly clamp for aero-engine Download PDFInfo
- Publication number
- CN113983239A CN113983239A CN202111285809.XA CN202111285809A CN113983239A CN 113983239 A CN113983239 A CN 113983239A CN 202111285809 A CN202111285809 A CN 202111285809A CN 113983239 A CN113983239 A CN 113983239A
- Authority
- CN
- China
- Prior art keywords
- clamp
- half part
- piece
- quick
- disassembling
- 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
Links
- 238000009434 installation Methods 0.000 claims abstract description 17
- 229910000639 Spring steel Inorganic materials 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 241000446313 Lamella Species 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- IAYPIBMASNFSPL-UHFFFAOYSA-N Ethylene oxide Chemical compound C1CO1 IAYPIBMASNFSPL-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
- F16L3/10—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two or more members engaging the pipe, cable or protective tubing
-
- 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
- F16L3/22—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals
- F16L3/237—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals for two pipes
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0406—Details thereof
Abstract
The invention belongs to the field of clamps, and particularly relates to a quick assembling and disassembling clamp for an aero-engine. The technical scheme of the invention is as follows: a quick assembling and disassembling clamp for an aircraft engine comprises an upper clamp half part and a lower clamp half part, wherein the upper clamp half part comprises an installation fitting piece and an upper clamp lobe; the mounting fitting piece is in a square barrel shape, and upper sawteeth are symmetrically arranged on two sides of the inner wall of the mounting fitting piece; the connecting piece is two forked elastic plates, and the outer walls of the two forked elastic plates are symmetrically provided with lower sawteeth; the upper half part of the clamp and the lower half part of the clamp are connected through the installation matching piece and the connecting piece, so that the quick assembly and disassembly can be realized. The quick assembling and disassembling clamp for the aero-engine provided by the invention has the functions of quick assembling and disassembling, can effectively reduce the assembling, disassembling and maintaining periods of the aero-engine, and improves the production efficiency.
Description
Technical Field
The invention belongs to the field of clamps, and particularly relates to a quick assembling and disassembling clamp for an aero-engine.
Background
The clamp of the aircraft engine is used for fixing pipelines, cables and other structural components of various systems of the engine and is an essential component of the engine. The use of the clamp can effectively reduce the probability of the conduit breaking due to vibration fatigue, directly influences the use quality of the engine, and is one of important factors influencing the reliability of the engine.
The prior conventional clamp structure is shown in figure 1, and generally comprises an upper clamp half 1, a lower clamp half 4, a fastening bolt 2, a locking plate 3 and felt 5, wherein 6 is a structure such as a conduit or a cable. The upper half 1 of the hoop is an integral plate, and the lower half of the hoop is of a welding structure through pressing, so that the threaded hole and the hoop are welded into a whole. The fastening bolt 2 is typically a navigation or russian piece which is locked with a locking tab 3 after the bolt is tightened. The felt 5 is intended to more effectively engage the upper and lower halves of the band and to prevent wear of the band and fastener.
The time to install a single clip is about 20 seconds and the time to remove a single clip is about 15 seconds. If the position of operating space is limited, the time for assembling and disassembling the conventional clamp can even reach more than 5 minutes, in the environment, the possibility that parts such as screws and locking plates on the clamp can fall off is high, and the time for searching the screws and the locking plates on an engine is longer. Because the quantity of the aircraft engine clamp is numerous, the installation and the disassembly of the conventional clamp can consume a large amount of time, the assembly and disassembly period of the aircraft engine is prolonged, particularly the arrangement period is multiplied at the position with limited operation space, and the production, repair and maintenance costs of the aircraft engine are further increased.
Disclosure of Invention
The invention provides a quick assembling and disassembling clamp for an aircraft engine, which has the functions of quick assembling and disassembling, can effectively reduce the assembling, disassembling and maintaining periods of the aircraft engine, and improves the production efficiency.
The technical scheme of the invention is as follows:
a quick assembling and disassembling clamp for an aircraft engine comprises an upper clamp half part and a lower clamp half part, wherein the upper clamp half part comprises an installation fitting piece and an upper clamp lobe; the mounting fitting piece is in a square barrel shape, and upper sawteeth are symmetrically arranged on two sides of the inner wall of the mounting fitting piece; the connecting piece is two forked elastic plates, and the outer walls of the two forked elastic plates are symmetrically provided with lower sawteeth; the upper half part of the clamp and the lower half part of the clamp are connected through the installation matching piece and the connecting piece, so that the quick assembly and disassembly can be realized.
Furthermore, the aeroengine is with installing and removing the clamp fast, the sharp angle direction of the said upper sawtooth is upwards, the sharp angle direction of the said lower sawtooth is downward, the said upper sawtooth and horizontal flank of the lower sawtooth have 5 included angles with horizontal direction; the upper saw teeth and the lower saw teeth are mutually matched in tooth shape. Make connecting piece and installation fitting piece are laminated more, also can avoid taking place the tooth phenomenon of taking off simultaneously.
Further, aeroengine with install and remove the clamp fast, the contained angle between two elastic plates of connecting piece is 5, its material is spring steel. The two elastic plates can be attached under the action of lateral pressure, and after the external force is removed, the elastic plates can naturally rebound to the original state. After the installation of clamp first half and clamp lower half is accomplished, outer expanding force between two elastic plates can strengthen the connecting piece with laminating degree between the installation fitting piece guarantees that the clamp can not appear the condition that both sides aperture differs when fixed.
Furthermore, the aeroengine is with installing and removing the clamp fast, the top of the elastic plate is the application of force face, as the department that exerts force of the tool; a conical surface is arranged between the force application surface and the lower saw teeth; the width between the topmost ends of the conical surfaces of the two elastic plates is smaller than the width of the mounting fitting piece. The installation clamp can be realized only by mutually pressing the upper clamp half part and the lower clamp half part.
Further, aeroengine with install and remove the clamp fast, the clamp first half is in the same place the back with the assembly of clamp lower half, the connecting piece exposes the length of installation fitting piece is greater than the connecting piece with cooperation length between the installation fitting piece can guarantee in the dismantlement in-process, the clamp first half separates with the clamp lower half completely before, the instrument can be all right the connecting piece is exerted and is made it be in the compression state.
Furthermore, aeroengine with install and remove the clamp fast, the clamp upper lamella and the clamp lower lamella are equipped with the protection pad.
The invention has the beneficial effects that: the rapid assembling and disassembling hoop for the aero-engine provided by the invention needs 2 seconds for installation and only 1 second for disassembly, can save the assembling and disassembling time by more than 97%, effectively reduces the assembling, disassembling and maintaining periods of the aero-engine, and improves the production efficiency.
Drawings
FIG. 1 is a view of a conventional clamp; in the figure: 1, clamping the upper half of a clamp, 2 fastening bolts, 3 locking plates, 4, the lower half of the clamp, 5 felts, 6 conduits or cables;
FIG. 2 is a schematic view of an aircraft engine assembled with a quick release clip;
FIG. 3 is an enlarged view of FIG. 2 at B;
FIG. 4 is a view showing the upper part of the clip;
FIG. 5 is a view of the lower half of the yoke;
FIG. 6 is a top view of the lower half of the clip;
FIG. 7 is a schematic view of an aircraft engine mounted with a quick release clip;
FIG. 8 is a schematic view of the quick release clip being removed from an aircraft engine.
Detailed Description
As shown in fig. 2-6, a quick-mounting and dismounting clamp for an aircraft engine comprises an upper clamp half and a lower clamp half, wherein the upper clamp half comprises a mounting fitting member 9 and an upper clamp lobe 10, the lower clamp half comprises a connecting member 7 and a lower clamp lobe 8, the mounting fitting member 9 is arranged in the middle of the upper clamp lobe 10, and the connecting member 7 is arranged in the middle of the lower clamp lobe 8; the mounting fitting piece 9 is in a square barrel shape, and upper sawteeth are symmetrically arranged on two sides of the inner wall of the mounting fitting piece; the connecting piece 7 is two forked elastic plates, and the outer walls of the two forked elastic plates are symmetrically provided with lower sawteeth; the sharp angle direction of the upper sawteeth is upward, the sharp angle direction of the lower sawteeth is downward, and the transverse tooth surfaces of the upper sawteeth and the lower sawteeth form an included angle of 5 degrees with the horizontal direction; the upper saw teeth and the lower saw teeth are mutually matched in tooth shape; the upper and lower clamp halves can be quickly assembled and disassembled by means of the fitting parts 9 and the connecting pieces 7.
The included angle between the two elastic plates of the connecting piece 7 is 5 degrees, and the connecting piece is made of spring steel; the top end of the elastic plate is a force application surface 14, and a conical surface 12 is arranged between the force application surface 14 and the lower saw teeth; the width between the topmost ends of the conical surfaces 12 of the two elastic plates is smaller than the width of the mounting fitting piece 9. After the upper clamp half part and the lower clamp half part are assembled together, the connecting piece 7 is exposed out of the installation matching piece 9, and the length of the connecting piece 7 is larger than that of the installation matching piece 9.
The upper clamp petal 10 and the lower clamp petal 8 are provided with protective pads 11; the fixing object 13 is common fuel oil pipeline, and can be metal felt of ethylene oxide 708A-B as protective pad 11; when the fixed object 13 is an air pipeline or a cable, a bushing made of GH696 can be selected as the protection pad 11.
The installation step: as shown in fig. 7, the lower clip lobe 8 is attached to the fixed object 13 to be assembled, and only the upper clip lobe 10 needs to be pressed down to a proper position, so that the lower saw teeth of the connecting member 7 are matched with the upper saw teeth of the fitting member 9, and the clip can be automatically locked through the tooth surface.
Disassembling: as shown in fig. 8, force F1 and F2 are applied to the force applying surface 14 of the connecting member 7 to disengage the lower teeth of the connecting member 7 from the upper teeth of the mounting engagement member 9, and then the clip lower piece 8 is removed.
Claims (6)
1. The quick assembling and disassembling clamp for the aircraft engine is characterized by comprising an upper clamp half part and a lower clamp half part, wherein the upper clamp half part comprises an installation fitting piece and an upper clamp lobe; the mounting fitting piece is in a square barrel shape, and upper sawteeth are symmetrically arranged on two sides of the inner wall of the mounting fitting piece; the connecting piece is two forked elastic plates, and the outer walls of the two forked elastic plates are symmetrically provided with lower sawteeth; the upper half part of the clamp and the lower half part of the clamp are connected through the installation matching piece and the connecting piece, so that the quick assembly and disassembly can be realized.
2. The quick connect and disconnect clamp of claim 1, wherein the upper serrations have a sharp angle in an upward direction and the lower serrations have a sharp angle in a downward direction, and the lateral flanks of the upper and lower serrations have an angle of 5 ° with the horizontal; the upper saw teeth and the lower saw teeth are mutually matched in tooth shape.
3. The quick connect and disconnect clamp of claim 1, wherein the angle between two spring plates of said connecting member is 5 °, and the material thereof is spring steel.
4. The quick-assembly and disassembly clamp for the aircraft engine as claimed in claim 3, wherein the top end of the elastic plate is a force application surface, and a conical surface is arranged between the force application surface and the lower saw teeth; the width between the topmost ends of the conical surfaces of the two elastic plates is smaller than the width of the mounting fitting piece.
5. The quick connect and disconnect clamp of claim 3, wherein after the clamp upper half and the clamp lower half are assembled together, the length of the connector exposed from the mounting fitting is greater than the length of the connector engaged with the mounting fitting.
6. The quick connect and disconnect clamp of claim 1, wherein the clamp upper and lower flaps are provided with protective pads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111285809.XA CN113983239A (en) | 2021-11-02 | 2021-11-02 | Quick assembly and disassembly clamp for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111285809.XA CN113983239A (en) | 2021-11-02 | 2021-11-02 | Quick assembly and disassembly clamp for aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113983239A true CN113983239A (en) | 2022-01-28 |
Family
ID=79745586
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111285809.XA Pending CN113983239A (en) | 2021-11-02 | 2021-11-02 | Quick assembly and disassembly clamp for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113983239A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWM256455U (en) * | 2004-04-29 | 2005-02-01 | Ting-Huei Chen | Improved structure of plastic pipe clamp |
| EP2492563A1 (en) * | 2011-02-25 | 2012-08-29 | Raywal Holding SAS | Clamp for a pipe or cable. |
| CN205118498U (en) * | 2015-11-20 | 2016-03-30 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine is quick -release clamp for external system |
| CN205168391U (en) * | 2015-10-20 | 2016-04-20 | 安徽华菱汽车有限公司 | Body mounting |
| CN211480777U (en) * | 2020-03-10 | 2020-09-11 | 浙江京伟科技发展有限公司 | Self-locking adjustable structure for triangular hoop |
-
2021
- 2021-11-02 CN CN202111285809.XA patent/CN113983239A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWM256455U (en) * | 2004-04-29 | 2005-02-01 | Ting-Huei Chen | Improved structure of plastic pipe clamp |
| EP2492563A1 (en) * | 2011-02-25 | 2012-08-29 | Raywal Holding SAS | Clamp for a pipe or cable. |
| CN205168391U (en) * | 2015-10-20 | 2016-04-20 | 安徽华菱汽车有限公司 | Body mounting |
| CN205118498U (en) * | 2015-11-20 | 2016-03-30 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine is quick -release clamp for external system |
| CN211480777U (en) * | 2020-03-10 | 2020-09-11 | 浙江京伟科技发展有限公司 | Self-locking adjustable structure for triangular hoop |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220128 |
|
| RJ01 | Rejection of invention patent application after publication |