CN114923039A - Self-assembly high-damping clamp for external pipeline of aircraft engine and manufacturing and using methods thereof - Google Patents
Self-assembly high-damping clamp for external pipeline of aircraft engine and manufacturing and using methods thereof Download PDFInfo
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- CN114923039A CN114923039A CN202210756205.7A CN202210756205A CN114923039A CN 114923039 A CN114923039 A CN 114923039A CN 202210756205 A CN202210756205 A CN 202210756205A CN 114923039 A CN114923039 A CN 114923039A
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- 238000013016 damping Methods 0.000 title claims abstract description 79
- 238000001338 self-assembly Methods 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 8
- 230000007246 mechanism Effects 0.000 claims abstract description 30
- 238000012545 processing Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 4
- 229920002635 polyurethane Polymers 0.000 claims description 4
- 239000004814 polyurethane Substances 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 229920001971 elastomer Polymers 0.000 claims description 3
- 239000005060 rubber Substances 0.000 claims description 3
- 239000003190 viscoelastic substance Substances 0.000 claims description 2
- 238000003754 machining Methods 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 10
- 238000009434 installation Methods 0.000 abstract description 4
- 230000007547 defect Effects 0.000 abstract description 2
- 238000011900 installation process Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 13
- 230000009467 reduction Effects 0.000 description 4
- 230000032683 aging Effects 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
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Classifications
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- 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
- F16L3/1091—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 with two members, the two members being fixed to each other with fastening members on each side
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention belongs to the field of design of clamps for aircraft engine pipelines, and particularly relates to a self-assembly high-damping clamp for an aircraft engine external pipeline and a manufacturing and using method thereof. The clamp comprises an embedded fan-shaped high-damping block, a self-assembly upper clamping band, a self-assembly lower clamping band, an assembly mechanism and a locking device, wherein grid areas are arranged on the self-assembly upper clamping band and the self-assembly lower clamping band, the embedded fan-shaped high-damping block is arranged in the clamping band from the side surface of the clamping band, and once the embedded fan-shaped high-damping block is arranged in the fan-shaped grid area of the clamping band, the embedded fan-shaped high-damping block is embedded in the fan-shaped grid area of the clamping band, and the fan-shaped area can effectively avoid the problem that the damping block falls off in the installation process due to the fact that the fan-shaped high-damping block bears the radial constraint force of a pipeline. In addition, the invention provides a plurality of fan-shaped grids which can effectively enhance the rigidity of the clamping bands, and the two clamping bands are provided with the guide grooves, so that the defects that the traditional clamping band is inaccurate in positioning, the clamping bands are staggered with each other, and the clamping bands are deviated in installation are overcome.
Description
Technical Field
The invention belongs to the field of design of a clamp for an aircraft engine pipeline, and particularly relates to a self-assembly high-damping clamp for an aircraft engine external pipeline and a manufacturing and using method thereof.
Background
The clamp hoop of the aero-engine plays roles in fixing, clamping and damping the pipeline, and is an important component of an external pipeline system of the aero-engine. Due to the bad service working condition, the external pipeline of the aircraft engine often vibrates to cause the problems of pipeline damage, breakage, oil leakage and the like, and further the stable operation of the aircraft engine is influenced. Although people carry out a great deal of research on the vibration reduction problem of the pipeline system, a certain pipeline vibration reduction effect is achieved through a coating, a damping material and a vibration active control mode. However, the types and the layout of the pipelines of the aero-engine are various, and the above means for adding damping is often limited by the limitations of application objects and use spaces, so that the effective implementation of the damping means is difficult to ensure. The clamp is a part directly connected with an aircraft engine pipeline, is innovatively designed, improves the damping effect, can directly absorb, isolate and block the influence of vibration of the engine case on the pipeline, and can inhibit the influence of fluid pulsation excitation in the pipeline on the structure of the engine case. Therefore, the development of a novel high-damping hoop is necessary. However, there is currently less attention to the damping design of the clamp, and there is also a problem in the efficient assembly of the clamp. At present, a novel self-assembly high-damping clamp capable of meeting the requirement of efficient vibration reduction of an external pipeline of an aero-engine is lacking. For example, patent CN211667328U proposes a clip that is easy to assemble, but this structure uses a hinge for connection, and multiple disassembly results in hinge abrasion, and does not consider the problems of damping effect and difficulty in disassembly of the clip; patent CN212691056U is a quick-assembling structure, which utilizes two plug-in connections and a bolt to fix the whole clamp. Although this design can ensure accurate positioning and easy assembly, the plug-in connection is fast in aging, and if this design is applied to an actual pipeline, a certain improvement must be made in the aspect of disassembly, the aging of the non-slip mat is accelerated in the disassembly process, and the non-slip mat has no fixing device, so that the damping effect cannot be stably exerted. Patent CN 214579559U also provides a resilient clamp which can accommodate both soft and rigid lines. However, the clamp lacks of a mounting and positioning structure, the accurate assembly of the clamp cannot be guaranteed, the vibration damping means is single, if a gap occurs between the clamp and a pipeline, the damping effect cannot be exerted, and the vibration damping effect is unreliable. Patent CN210859441U provides a nonmetal clamp hoop, is provided with quick-release bolt on the corner piece, sets up a plurality of buckles on the anchor ring of another end of clamp hoop, buckle and quick-release bolt looks adaptation. The design can ensure the assembly precision of the clamp to a certain extent, but has higher cost, does not consider the vibration reduction design of the clamp, and can not meet the vibration suppression requirement of a pipeline. Patent CN209781367U proposes a method for quickly assembling a clamp, which fixes a special device by two connecting plates, and then controls the assembling by bolts to make the assembling quick, but the disassembling speed is affected because the joint structure is complex, and the vibration may be aggravated because the clamp is not well matched with the pipeline.
In addition, a plurality of scientific researchers provide methods for structurally enhancing the damping effect of the clamp, but only the damping effect is usually paid attention to, and the quick and high-precision assembling effect of the clamp and the pipeline is difficult to ensure. For example, patent CN204300557U provides an integral damping clamp capable of automatic compensation, reducing vibration and prolonging the service life of the pipeline, but the lack of assembly guide structure or device results in long assembly time, and high assembly efficiency cannot be guaranteed. Patent CN201582496U provides an elasticity clamp, and damping performance is good, but the structure is comparatively single, because only bolted connection's one side is separable, other is whole, and it is comparatively difficult to dismantle. Patent 110822208A provides a damping band design and provides a temperature resistant layer that improves the damping performance of the band and reduces the degradation of the band. However, the assembly problem of the clamp is neglected, the assembly is very time-consuming, and the connection mode has the problem that the connection and the positioning of the pipeline are loose. Patent CN104214427A is a metal liner clamp, has better damping effect, but the shortcoming is the atress of the kind of metal liner after the uncontrollable assembly, and metal liner and pipeline can not laminate comprehensively, and it is inhomogeneous to have the pipeline damping effect, and is difficult to guarantee the assembly effect.
To sum up, the above-mentioned patent technology is difficult to satisfy the actual demand of aeroengine clamp self-assembly, high damping, and then can not realize the dual purpose of the damping of outside pipe-line system and easy assembly.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a self-assembly high-damping clamp for an external pipeline of an aircraft engine and a manufacturing and using method thereof.
The technical scheme of the invention is as follows:
the utility model provides a clamp for external pipeline from assembly, high damping aeroengine which characterized in that, including embedded fan-shaped high damping piece, from the assembly go up the clamp strap, from the assembly clamp strap, assembly devices and locking device down:
two guide grooves A are arranged at one end of the self-assembly upper clamping strap, a groove A and two convex grooves B are arranged at the other end of the self-assembly upper clamping strap, and a plurality of grid areas are arranged on the clamping strap;
one end of the self-assembly lower clamping strap is provided with two guide grooves B, the other end of the self-assembly lower clamping strap is provided with a convex groove A and a cylindrical through hole A, and the clamping strap is provided with a plurality of grid areas;
the assembling mechanism is in a hollow cuboid shape, two grooves B are formed in two sides inside the assembling mechanism, and a cylindrical through hole B with threads is formed in the other side of the assembling mechanism;
the locking device comprises a smooth cylinder at the front end, a cylinder with threads in the middle and a bottom handle;
grid areas on the self-assembly upper clamping band and the self-assembly lower clamping band are formed by connecting radial grid walls and transverse grid walls, separated fan-shaped spaces form grids, and embedded fan-shaped high-damping blocks are installed in the grids; the guide groove A and the guide groove B correspond to each other, and one end of the self-assembly upper clamping band and one end of the self-assembly lower clamping band are assembled through the guide groove A and the guide groove B; recess A cooperatees with tongue A, and two recess B of assembly devices cooperate with two tongue B from the assembly upper clamping band, realize the fixed of assembly devices position, and locking device's smooth cylinder cooperates with the cylindrical through-hole A from the assembly lower clamping band, and threaded cylinder cooperates with assembly devices's threaded cylindrical through-hole B, accomplishes from the assembly upper clamping band and from the assembly of the lower clamping band other end.
Further, foretell from assembly, high damping clamp for aeroengine external pipeline, guiding groove A and guiding groove B all set up to the ladder groove, and guiding groove A and guiding groove B correspond each other for realize assembly clamp and location sooner.
Furthermore, the self-assembly high-damping clamp for the external pipeline of the aircraft engine has the advantages that the cylindrical through hole A of the lower clamp belt, the cylindrical through hole B of the assembly mechanism, the smooth cylinder of the locking device and the cylinder with the threads are coaxial.
Furthermore, according to the self-assembling high-damping clamp for the external pipeline of the aircraft engine, the diameter of the cylindrical through hole B of the assembling mechanism is the same as that of the cylindrical through hole A of the self-assembling lower clamping band.
Furthermore, according to the self-assembling high-damping clamp for the external pipeline of the aircraft engine, the embedded fan-shaped high-damping block can be obtained by cutting a heat-resistant polyurethane material and a heat-resistant elastic rubber material;
a manufacturing method of a self-assembly high-damping hoop for an aircraft engine external pipeline comprises the following steps:
step 1: processing a die for assembling the upper clamping band, and preparing the self-assembling upper clamping band by the die by a stamping method, wherein two convex grooves matched with the assembling mechanism, two concave grooves matched with the lower clamping band and a stepped guide groove of the concave grooves on the upper clamping band are formed by one-step stamping;
step 2: the die is used for processing the self-assembled lower clamping band, the self-assembled lower clamping band is prepared by the die through a stamping method, and a hole which is arranged on the lower clamping band and is matched with the locking device, a convex groove which is matched with the upper clamping band and a stepped guide groove of the convex groove are formed through one-time stamping;
step 3: two grooves B of the assembling mechanism which are matched with the self-assembling clamping band are processed by a stamping method,
the other parts of the assembling mechanism are assembled together in a mortise and tenon joint mode to form a hollow cuboid shape, and the self-assembling upper clamping band and the self-assembling lower clamping band are assembled by the assembling mechanism;
and 4, step 4: purchasing a cylinder outside, and processing a locking device through a turning process;
and 5: the embedded fan-shaped high damping block is cut out by a cutting process and embedded into the grid area from the opening of the grid area of the self-assembled upper clamping band and the self-assembled lower clamping band.
A using method of a self-assembly high-damping clamp hoop for an external pipeline of an aircraft engine is characterized in that a self-assembly upper clamp belt is installed on the external pipeline of the aircraft engine, and then a self-assembly lower clamp belt is matched with the self-assembly upper clamp belt and is fixed by an assembly mechanism; and finally, the self-assembly upper clamping band and the self-assembly lower clamping band are locked through the locking device, the whole self-assembly high-damping aero-engine external pipeline is locked by the clamp through the handle of the locking device, the other end of the self-assembly upper clamping band and the self-assembly lower clamping band is provided with bolt holes, and the clamp is fixed on the aero-engine external pipeline through the bolt holes.
The invention has the beneficial effects that:
1. the high-damping clamp is suitable for an external pipeline system of an aircraft engine, is not limited to the field, and can be widely applied to the pipeline system with pressure pulsation impact. In addition, the hollow part can prevent the stress concentration of the clamp belt, increase the rigidity of the clamp belt, ensure the rigidity performance requirement of the grating and prolong the service life of the clamp belt.
2. The self-assembly structure is accurate in positioning and high in assembly speed, does not need to be installed by using a tool, meets the requirement of convenience in disassembly, and overcomes the defects that the traditional clamp is inaccurate in positioning and has deviation in installation. In addition, through holes are reserved in the two bands, and the two bands can be fixed in a bolt tightening mode.
3. The design of the guide groove of the invention ensures the installation accuracy, solves the problem of dislocation or sliding between the two bands in the installation process, and also solves the problem of low assembly speed of the existing clamp. And considering the relevant requirement of economic nature, can adopt the mode processing guiding groove of punching press to design the structure of a section ladder groove, the removal of restraint clamp that can be fine.
4. The embedded fan-shaped high-damping blocks are key for ensuring good vibration damping performance of the whole hoop, the high-damping blocks are matched with the grid region and filled into the grid region from an opening of the grid region, the high-damping filling blocks are fan-shaped, wide in upper part and narrow in lower part and perfectly fit in a vacancy formed by the grid structure, so that the high-damping filling blocks cannot fall from the hoop, and the high-damping filling blocks are made of polyurethane materials, viscoelastic materials or rubber and can achieve the effects of temperature resistance and aging resistance at the temperature of 250 ℃.
Drawings
FIG. 1 is an external view of a self-assembling, high damping clamp for external piping of an aircraft engine according to an embodiment of the present invention
FIG. 2 is a schematic view of the assembly mechanism according to the embodiment of the present invention;
FIG. 3 is a schematic structural view of a locking device according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of the structure of the embedded fan-shaped high damping block according to the embodiment of the present invention;
FIG. 5 is a schematic view of a self-assembling upper clamping band in accordance with an embodiment of the present invention;
FIG. 6 is a schematic view of a self-assembling lower clamping band in accordance with an embodiment of the present invention.
Wherein: 1-embedded fan-shaped high damping block; 2-a grid area; 3-an assembling mechanism; 4-a locking device; 5-self-assembling a clamping band; 6-self-assembling lower clamping band; 7-a guide groove A; 8-a guide groove B; 9-groove B; 10-tongue B; 11-cylindrical through hole a; 12-a smooth cylinder (12); 13-a threaded cylinder; 14-a threaded cylindrical through hole B; 15-bottom handle; 16-a radial grating wall; 17-transverse grid walls 17; 18-groove a 18; 19-tongue a 19; 20-bolt hole.
Detailed Description
The following detailed description of the invention refers to the accompanying drawings 1-6.
As shown in fig. 1, a self-assembling high damping clamp for an external pipeline of an aircraft engine comprises an embedded fan-shaped high damping block 1, a self-assembling upper clamping band 5, a self-assembling lower clamping band 6, an assembling mechanism 3 and a locking device 4:
as shown in fig. 5, the self-assembled upper clamping band 5 has two guide grooves a7 at one end, a groove a18 and two convex grooves B10 at the other end, and a plurality of grid regions 2;
as shown in fig. 6, the self-assembled lower clamping band 6 has two guiding grooves B8 at one end, a convex groove a19 and a cylindrical through hole a11 at the other end, and a plurality of grid regions 2;
guide groove a7 and guide groove B8 are each provided as a stepped groove.
As shown in fig. 2, the assembly mechanism 3 is a hollow cuboid, two grooves B9 are arranged on two sides inside the assembly mechanism 3, and a cylindrical through hole B14 with threads is arranged on the other side;
as shown in fig. 3, the locking device 4 comprises a smooth cylinder 12 at the front end, a cylinder 13 with threads in the middle and a bottom handle 15;
the grid region 2 on the clamp belt 5 is connected with the grid region 2 on the clamp belt 6 by the radial grid wall 16 and the horizontal grid wall 17, the separated fan-shaped space forms a grid, the rigidity of the whole clamp belt can be enhanced in the grid region, fatigue failure of the clamp belt due to insufficient strength is prevented, the embedded fan-shaped high damping block 1 is installed into the clamp belt from the side face of the clamp belt, once the embedded fan-shaped high damping block 1 is installed, the embedded fan-shaped high damping block 1 can be automatically restrained from falling, the embedded fan-shaped high damping block 1 is made of polyurethane materials, and damping of the clamp belt can be enhanced. The guide groove A7 and the guide groove B8 correspond to each other, and the self-assembled upper clamping band 5 and the self-assembled lower clamping band 6 are assembled at one end through the guide groove A7 and the guide groove B8; recess A18 cooperatees with tongue A19, two recess B9 of assembly devices 3 and two tongue B10 cooperations from the assembly upper clamping strap 5, realize the fixed of assembly devices 3 position, it is accurate to fix a position, locking device 4's smooth cylinder 12 and the cylindrical through-hole A11 cooperation from the assembly lower clamping strap 6, threaded cylinder 13 and assembly devices 3's threaded cylindrical through-hole B14 cooperation, the completion is from the assembly upper clamping strap 5 and from the assembly lower clamping strap 6 other end's assembly. The cylindrical through hole A11 of the lower clamping band 6, the cylindrical through hole B14 of the assembling mechanism 3, the smooth cylinder 12 of the locking device 4 and the threaded cylinder 13 are coaxially assembled. The diameter of the cylindrical through hole B14 of the assembling mechanism 3 is the same as that of the cylindrical through hole A11 of the self-assembling lower clamping band (6).
The manufacturing method of the hoop for the external pipeline of the self-assembly high-damping aircraft engine comprises the following steps:
step 1: firstly, processing a die for assembling the upper clamping band 5 and the lower clamping band 6, and then processing the upper clamping band 5 and the lower clamping band 6 by a stamping method;
step 2: two grooves B9 of the assembling mechanism 3 are processed by a stamping method, other parts of the assembling mechanism 3 are assembled together in a mortise-tenon connection mode to form a hollowed cuboid shape, the assembling mechanism 3 is used for assembling the clamping band 5 under self assembly and the clamping band 6 under self assembly, during installation, the assembling mechanism 3 needs to be installed on the clamping band 6 under self assembly firstly, the clamping band is coaxial, and then the smooth cylinder 12 at the front end of the locking device 4 is abutted to the cylindrical through hole A11 of the clamping band 6 under self assembly. The middle threaded cylinder 13 of the locking device 4 then engages with the bottom threaded cylindrical through hole B14 of the assembly means 3. The two bands can be fitted together by means of a handle 15;
and step 3: the locking device 4 is machined by a turning process or a similar threaded standard part is directly purchased and machined;
and 4, step 4: the embedded fan-shaped high damping mass 1 is cut out by a cutting process and embedded into a grid of self-assembled upper clamping bands 5 and self-assembled lower clamping bands 6.
The using method of the self-assembly high-damping clamp for the external pipeline of the aircraft engine is characterized in that the self-assembly upper clamp belt 5 is firstly installed on the external pipeline of the aircraft engine, and then the self-assembly lower clamp belt 6 is matched with the self-assembly upper clamp belt 5 and is fixed by the assembling mechanism 3; and finally, the self-assembly upper clamping band 5 and the self-assembly lower clamping band 6 are locked through the locking device 4, the whole self-assembly high-damping aero-engine external pipeline is locked by the clamp through the handle 15 of the locking device, the other end of the self-assembly upper clamping band 5 and the self-assembly lower clamping band 6 is provided with bolt holes 20, and the clamp is fixed on the aero-engine external pipeline through the bolt holes 20.
Claims (7)
1. The utility model provides a self-assembly, high damping clamp for aeroengine external pipeline which characterized in that, including embedded fan-shaped high damping piece (1), from assembling go up clamp strap (5), from assembling clamp strap (6) down, assembly devices (3) and locking device (4):
two guide grooves A (7) are arranged at one end of the self-assembly upper clamping strap (5), a groove A (18) and two convex grooves B (10) are arranged at the other end of the self-assembly upper clamping strap, and a plurality of fan-shaped grating areas (2) are arranged on the clamping strap;
one end of the self-assembly lower clamping strap (6) is provided with two guide grooves B (8), the other end of the self-assembly lower clamping strap is provided with a convex groove A (19) and a cylindrical through hole A (11), and the strap is provided with a plurality of fan-shaped grating areas (2);
the assembly mechanism (3) is in a hollow cuboid shape, two grooves B (9) are formed in two sides of the interior of the assembly mechanism (3), and a cylindrical through hole B (14) with threads is formed in the other side of the interior of the assembly mechanism;
the locking device (4) comprises a smooth cylinder (12) at the front end, a cylinder (13) with threads in the middle and a bottom handle (15);
the sector-shaped grating area (2) on the self-assembly upper clamping band (5) and the self-assembly lower clamping band (6) is formed by connecting a radial grating wall (16) and a transverse grating wall (17), the separated sector-shaped spaces form a grating, and the embedded sector-shaped high damping block (1) is installed in the grating; the guide groove A (7) and the guide groove B (8) correspond to each other, and one end of the self-assembly upper clamping band (5) and one end of the self-assembly lower clamping band (6) are assembled through the guide groove A (7) and the guide groove B (8); recess A (18) cooperate with tongue A (19), two recess B (9) of assembly devices (3) and two tongue B (10) cooperations from the assembly on calorie strap (5), realize the fixed of assembly devices (3) position, smooth cylinder (12) of locking device (4) and cylindrical through-hole A (11) cooperation from the assembly under calorie strap (6), threaded cylinder (13) and cylindrical through-hole B (14) cooperation of the screw thread of assembly devices (3), the completion is from the assembly on calorie strap (5) and the assembly of the lower calorie strap (6) other end from the assembly.
2. The self-assembling, high-damping clamp for an aircraft engine external pipeline according to claim 1, wherein the guide grooves a (7) and B (8) are both provided as stepped grooves.
3. A self-assembling, high-damping clamp for external pipes of aircraft engines, according to claim 1, characterised in that the cylindrical through hole A (11) of the lower clamping band (6) of the self-assembling, the cylindrical through hole B (14) of the assembly means (3), the smooth cylinder (12) of the locking device (4) and the threaded cylinder (13) are coaxial.
4. A self-assembling, high-damping clamp for external pipes of aircraft engines, according to claim 1, characterized in that the cylindrical through hole B (14) of the assembly means (3) has the same diameter as the cylindrical through hole A (11) of the self-assembling lower clamping band (6).
5. The clamp for the external pipelines of the self-assembling high-damping aircraft engine according to claim 1, characterized in that the material of the embedded fan-shaped high-damping block (1) is polyurethane material, viscoelastic material or rubber material.
6. A method of making a self-assembling, high-damping aircraft engine external pipe clamp according to claim 1, comprising the steps of:
step 1: firstly, processing a die for assembling the upper clamping band (5) and the lower clamping band (6), and then processing the upper clamping band (5) and the lower clamping band (6) by a stamping method;
step 2: processing two grooves B (9) of the assembling mechanism (3) by a stamping method, assembling other parts of the assembling mechanism (3) together in a tenon-and-mortise connection mode to form a hollowed cuboid shape, and assembling the self-assembled upper clamping band (5) and the self-assembled lower clamping band (6) by using the assembling mechanism (3);
and 3, step 3: machining the locking device (4) through a turning process;
and 4, step 4: the embedded fan-shaped high damping block (1) is cut through a cutting process and is embedded into a grid of a self-assembly upper clamping band (5) and a self-assembly lower clamping band (6).
7. The use method of the clamp for the external pipe of the self-assembly high-damping aircraft engine as defined in claim 1 is characterized in that the self-assembly upper clamping band (5) is installed on the external pipe of the aircraft engine, and then the self-assembly lower clamping band (6) is matched with the self-assembly upper clamping band (5) and fixed by the assembly mechanism (3); and finally, the clamping band (5) is assembled and the clamping band (6) is locked under the self-assembly through the locking device (4), the whole self-assembly and high-damping clamp band for the external pipeline of the aero-engine is locked through a handle (15) of the locking device, the bolt holes (20) are formed in the other end of the clamping band (6) under the self-assembly of the clamping band (5), and the clamp band is fixed on the external pipeline of the aero-engine through the bolt holes (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210756205.7A CN114923039A (en) | 2022-06-29 | 2022-06-29 | Self-assembly high-damping clamp for external pipeline of aircraft engine and manufacturing and using methods thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210756205.7A CN114923039A (en) | 2022-06-29 | 2022-06-29 | Self-assembly high-damping clamp for external pipeline of aircraft engine and manufacturing and using methods thereof |
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| Publication Number | Publication Date |
|---|---|
| CN114923039A true CN114923039A (en) | 2022-08-19 |
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| CN202210756205.7A Pending CN114923039A (en) | 2022-06-29 | 2022-06-29 | Self-assembly high-damping clamp for external pipeline of aircraft engine and manufacturing and using methods thereof |
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| CN (1) | CN114923039A (en) |
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| CN108730622A (en) * | 2018-06-06 | 2018-11-02 | 合肥博恒电气科技有限公司 | A kind of wire barrel fixed fastener |
| CN208886129U (en) * | 2018-09-15 | 2019-05-21 | 山东鲁源消防科技有限公司 | A kind of reinforced clip |
| CN211501217U (en) * | 2019-12-30 | 2020-09-15 | 石家庄军马勇机械科技有限公司 | Square-opening corrugated pipe sealing joint for prestressed bridge |
-
2022
- 2022-06-29 CN CN202210756205.7A patent/CN114923039A/en active Pending
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| EP2913574A1 (en) * | 2014-02-26 | 2015-09-02 | Electrix International Limited | Conduit mounting device |
| CN104370199A (en) * | 2014-11-11 | 2015-02-25 | 瑞电士（常熟）传感器有限公司 | Escalator speed measuring system |
| CN204533827U (en) * | 2015-04-01 | 2015-08-05 | 浙江树人大学 | A kind of optical fibre communication cable clip for computer |
| CN108730622A (en) * | 2018-06-06 | 2018-11-02 | 合肥博恒电气科技有限公司 | A kind of wire barrel fixed fastener |
| CN208886129U (en) * | 2018-09-15 | 2019-05-21 | 山东鲁源消防科技有限公司 | A kind of reinforced clip |
| CN211501217U (en) * | 2019-12-30 | 2020-09-15 | 石家庄军马勇机械科技有限公司 | Square-opening corrugated pipe sealing joint for prestressed bridge |
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Application publication date: 20220819 |