CN220066759U

CN220066759U - Pipeline harness clamp for aircraft engine

Info

Publication number: CN220066759U
Application number: CN202321543717.1U
Authority: CN
Inventors: 王欢; 李亮
Original assignee: Northwest Rubber and Plastics Research and Design Institute
Current assignee: Northwest Rubber and Plastics Research and Design Institute
Priority date: 2023-06-16
Filing date: 2023-06-16
Publication date: 2023-11-21
Anticipated expiration: 2033-06-16

Abstract

The utility model discloses a pipeline harness clamp for an aircraft engine, which comprises a clamp framework and a composite clamp sleeve, wherein the clamp framework is of a strip-shaped structure, one end of the clamp framework is provided with a clamp, and the inner side surface of the other end of the clamp framework is provided with a clamping tooth part; the composite clamp sleeve is of a strip-shaped structure and comprises a clamp sleeve body and a pressure change part arranged on the inner side surface of the clamp sleeve body, wherein the clamp sleeve body sequentially comprises an inner silicone rubber layer, a glass fiber fabric layer and an outer silicone rubber layer from inside to outside, and a through cavity is formed along the clamp sleeve body; the pressure change portion includes a plurality of convex body, and the clamp skeleton wears to locate the intracavity that link up of clamp sleeve body, and clamp dop and latch portion all are located the clamp sleeve body outside. The clamp sleeve is of a multi-layer composite structure, the strength and ageing resistance of the clamp sleeve are improved, cracks and even breakage of the clamp sleeve are avoided, and meanwhile, the clamp sleeve is provided with the pressure change part which is in direct contact with the pipeline wire harness, so that the effects of noise reduction, vibration reduction and protection of the pipeline wire harness are achieved.

Description

Pipeline harness clamp for aircraft engine

Technical Field

The utility model belongs to the technical field of clamps, and particularly relates to a pipeline harness clamp for an aircraft engine.

Background

The pipeline wire harness clamp system of the aircraft engine plays an important role in conveying various mediums such as oil, liquid and gas, and in the aircraft engine, various pipeline wire harnesses are commonly used for clamping the clamp. Because various complex loads such as high temperature, high pressure, high speed and the like generated during the operation of the engine act on the pipeline system, faults such as vibration, fatigue, leakage and the like of the pipeline system are easily caused. Therefore, the clip serves as an important connection part of the pipeline system, and plays an important role in frequency modulation and vibration reduction.

At present, most of the traditional clamp main bodies are of metal structures and are directly contacted with an aircraft engine pipeline for fixing, for example: the journal of the profession, the flight design, and the 2009, 12 months, discloses an aviation conduit link clamp research (Zheng Min et al, which discloses a structure, materials, performance and identification test item of a novel aluminum alloy flexible conduit link clamp, so as to solve the defects and problems of the traditional clamp. The article indicates that the traditional clamp is mostly of a metal structure, and the problems of welding stress, stress corrosion, poor neutrality, aging of a sealing gasket and the like exist.

In actual working condition, because the long-time vibrations of engine can lead to the clamp to become flexible, fastening effect is relatively poor, probably leads to the pipeline pencil to suffer friction damage simultaneously, causes the engine potential safety hazard.

Disclosure of Invention

The utility model provides a pipeline harness clamp for an aircraft engine, which solves the problems that the traditional metal clamp is easy to loosen and the pipeline harness is easy to be damaged by friction.

In order to achieve the above purpose, the technical scheme of the utility model is as follows:

the pipeline harness clamp for the aircraft engine is characterized by comprising a clamp framework and a composite clamp sleeve, wherein the clamp framework is of a strip-shaped structure, one end of the clamp framework is provided with a clamp head, and the inner side surface of the other end of the clamp framework is provided with a clamping tooth part; the composite clamp sleeve is of a strip-shaped structure and comprises a clamp sleeve body and a pressure change part arranged on the inner side surface of the clamp sleeve body, wherein the clamp sleeve body sequentially comprises an inner silicon rubber layer, a glass fiber fabric layer and an outer silicon rubber layer from inside to outside, and a through cavity is formed along the length central line direction of the clamp sleeve body; the pressure change portion comprises a plurality of convex bodies, the clamp framework is arranged in the through cavity of the clamp sleeve body in a penetrating mode, and the clamp clamping head and the clamping tooth portion are located outside the clamp sleeve body.

Further, a plurality of convex bodies are sequentially arranged along the width direction of the clamp sleeve body, and the length of each convex body is equal to the length of the clamp sleeve body.

Further, a plurality of protruding bodies are arranged in sequence along the length direction of the clamp sleeve body, and the length of each protruding body is equal to the width of the clamp sleeve body.

Further, the convex bodies are parallel to each other and have equal spacing.

Further, the width of the bottom surface of the convex body is 1 to 2.5 times of the distance between the adjacent convex bodies.

Further, the longitudinal section of the convex body is triangular.

Further, the longitudinal section of the convex body is trapezoid.

Further, the width of the bottom surface of the convex body is 0.5-5 times of the height of the convex body.

Furthermore, the clamp skeleton is made of metal material.

Compared with the prior art, the utility model has the following beneficial effects:

1. the utility model provides a pipeline wire harness clamp for an aircraft engine, which comprises a clamp framework and a composite clamp sleeve, wherein the clamp framework is arranged in the composite clamp sleeve in a penetrating way, and a pressure change part arranged on the surface of the composite clamp sleeve is in direct contact with a pipeline wire harness, so that noise can be reduced, vibration of a pipeline can be buffered, and friction damage of the pipeline wire harness is avoided.

2. The composite clamp sleeve is formed by tightly compounding an inner silicon rubber layer, a glass fiber fabric layer and an outer silicon rubber layer from inside to outside, wherein the glass fiber fabric layer can play a role in reinforcing the clamp sleeve body, and the strength and the tearing resistance of the clamp sleeve are improved, so that the tearing damage of the clamp framework and the clamp sleeve in the assembling process is avoided; the silicone rubber has good elasticity, ozone aging resistance and heat air aging resistance, and in actual working conditions, chemical reaction can not occur due to the rise of atmospheric environment and temperature, and the phenomenon of cracks and even fracture on the surface of the clamp sleeve is avoided.

It is, of course, not necessary for all of the above advantages to be achieved simultaneously in the practice of the various aspects of the utility model.

Drawings

In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present disclosure, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.

Fig. 1 is a schematic view showing the overall structure of a clip according to embodiment 1 of the present utility model.

FIG. 2 is a schematic cross-sectional view at A-A of FIG. 1.

Fig. 3 is a schematic overall structure of the clip according to embodiment 2 of the present utility model.

Fig. 4 is a schematic cross-sectional view at B-B of fig. 3.

Fig. 5 is a longitudinal sectional view of the production die of example 1 of the present utility model.

Fig. 6 is a schematic diagram of the positional relationship between the lower mold and the mold core in fig. 5.

In the figure, the clamping device comprises a 1-clamp framework, a 11-clamp head, a 12-clamp tooth part, a 2-composite clamp sleeve, a 21-pressure change part, a 2101-convex body, a 22-clamp sleeve body, a 2201-outer silicone rubber layer, a 2202-glass fiber fabric layer, a 2203-inner silicone rubber layer, a 3-upper die, a 4-die core, a 5-lower die, a 6-die cavity and a 7-die core positioning part.

Detailed Description

Various aspects and features of the disclosure are described herein with reference to the drawings.

It should be understood that various modifications may be made to the embodiments of the application herein. Therefore, the above description should not be taken as limiting, but merely as exemplification of the embodiments. Other modifications within the scope and spirit of this disclosure will occur to persons of ordinary skill in the art.

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and, together with a general description of the disclosure given above and the detailed description of the embodiments given below, serve to explain the principles of the disclosure.

These and other characteristics of the present disclosure will become apparent from the following description of a preferred form of embodiment, given as a non-limiting example, with reference to the accompanying drawings.

It should also be understood that, although the present disclosure has been described with reference to some specific examples, a person skilled in the art will certainly be able to achieve many other equivalent forms of the present disclosure, having the characteristics as set forth in the claims and hence all coming within the field of protection defined thereby.

The above and other aspects, features and advantages of the present disclosure will become more apparent in light of the following detailed description when taken in conjunction with the accompanying drawings.

Specific embodiments of the present disclosure will be described hereinafter with reference to the accompanying drawings; however, it is to be understood that the disclosed embodiments are merely examples of the disclosure, which may be embodied in various forms. Well-known and/or repetitive functions and structures

And are not described in detail to avoid obscuring the present disclosure with unnecessary or redundant detail. Therefore, specific structural and functional details disclosed herein are not intended to be limiting, but merely serve as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present disclosure in virtually any appropriately detailed structure.

The specification may use the word "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," which may each refer to one or more of the same or different embodiments in accordance with the disclosure.

Example 1:

referring to fig. 1, a pipeline harness clamp for an aircraft engine comprises a clamp framework 1 and a composite clamp sleeve 2, wherein the clamp framework 1 is of a strip-shaped structure made of metal materials, a clamp clamping head 11 is arranged at one end of the clamp framework 1, a clamping tooth part 12 is arranged on the inner side surface of the other end of the clamp framework 1, and the clamping tooth part 12 can penetrate through the clamp clamping head 11 and be meshed and fixed with the clamp clamping head 11; the composite clamp sleeve 2 is of a strip-shaped structure, the whole length of the composite clamp sleeve is slightly shorter than that of the clamp framework 1, the composite clamp sleeve comprises a clamp sleeve body 22 and a pressure change part 21 arranged on the inner side surface of the clamp sleeve body 22, and the pressure change part 21 comprises a plurality of convex bodies 2101; the clamp sleeve body 22 is provided with a through cavity with a rectangular section along the length center line direction, the clamp skeleton 1 is arranged in the through cavity of the clamp sleeve body 22 in a penetrating mode, and the clamp head 11 and the clamping tooth part 12 are located outside the clamp sleeve body 22.

Referring to fig. 2, the collar body 22 includes, in order from inside to outside, an inner silicone rubber layer 2203, a glass fiber fabric layer 2202, and an outer silicone rubber layer 2201, the materials of the layers being closely compounded; the glass fiber fabric layer 2202 can increase the strength of the collar body 22, and the silicone rubber is used as an elastic material, has the ozone aging resistance and the heat-air aging resistance, and can not generate chemical reaction due to the atmospheric environment and the temperature rise in the actual working condition, so that the phenomenon of cracking or even breaking of the surface of the composite collar 2 is avoided.

The pressure changing part 21 comprises a plurality of convex bodies 2101 which are sequentially arranged in parallel along the width direction of the clamp sleeve body 22, the length of each convex body 2101 is equal to that of the clamp sleeve body 22, the longitudinal section of each convex body 2101 is triangular, the width of the bottom of each convex body 2101 is (0.6+/-0.1) cm, and the height of each convex body 2101 is (1.0+/-0.1) cm.

When the clamp is used, the clamp surrounds the pipeline wire harness for a circle, the clamping tooth part 12 penetrates through the clamp clamping head 11 and clamps the pipeline wire harness through meshing with the clamp clamping head 11, so that the pressure change part 21 is in direct contact with the pipeline wire harness, and the effects of noise reduction, vibration reduction and pipeline wire harness protection are achieved. Since the present embodiment adopts the collar body 22 and the pressure changing part 21 made of the composite material, it is possible to adaptively deform according to the shape and size of the line harness, and provide sufficient rigidity and damping to resist various complex loads such as high temperature, high pressure, high speed, etc. generated when the engine is operated. Meanwhile, the clamping hoop framework 1 and the clamping hoop sleeve body 22 are connected by the locking device which is quickly disassembled and assembled, so that the tightening torque of the clamping hoop can be conveniently adjusted, and the defects of stress concentration and the like in the traditional clamping hoop are avoided. Therefore, the present embodiment can effectively improve vibration characteristics, sealing performance, and durability of the piping system, and reduce maintenance workload and cost.

Referring to fig. 5 and 6, the following describes the preparation process of the pipe harness clip for an aircraft engine according to this embodiment:

s1, closing a die and preheating the die for 30min at 160 ℃, then, spraying a release agent on the surfaces of a cavity 6 and a die core 4, and drying for 3-5 min for later use;

s2, wrapping the thin film along the outer surface of the mold core 4 for one circle, wrapping the cut glass fiber fabric along the outer surface of the thin film for one circle, and finally wrapping the cut glass fiber fabric along the outer surface of the glass fiber fabric for one circle by using another thin film for later use;

step S3, spreading the thick film in a cavity 6 of a lower die 5, and then placing the die core 4 coated in the step 2 at a die core positioning position 7 of the lower die 5, and closing the die for vulcanization, wherein the vulcanization condition is 160 ℃ for 30min;

and S4, after vulcanization is finished, opening the mold, and taking down the product by using a demolding tool.

Example 2:

referring to fig. 3 and 4, unlike embodiment 1, the pressure varying part 21 includes a plurality of bosses 2101 arranged in parallel in sequence along the length direction of the collar body 22, the length of each boss 2101 is equal to the width of the collar body 22, the longitudinal section of the boss 2101 is trapezoidal, the width of the bottom of the boss 2101 is (1.0±0.1) cm, the height is (0.3±0.1) cm, and the interval between adjacent bosses 2101 is (0.5±0.1) cm.

In this embodiment, the protrusions 2101 are sequentially arranged in parallel along the length direction of the collar body 22, and the arrangement direction of the protrusions 2101 is the bending direction of the collar body 22, so as to improve the self-adapting capability of the pressure changing portion 21 to the shape and size of the pipe bundle. Meanwhile, the longitudinal section of the convex body 2101 of the pressure changing part 21 is trapezoidal, so that the contact area between the convex body 2101 and the pipeline wire harness can be increased, the rigidity and the damping of the pressure changing part 21 are improved, and the vibration and the noise of the pipeline system are further reduced.

The foregoing is illustrative of the present utility model, but the present utility model is not limited to the above-mentioned embodiments, and can be applied to similar products, and any person skilled in the art will be able to make variations or modifications within the scope of the present utility model.

Claims

1. The pipeline harness clamp for the aircraft engine is characterized by comprising a clamp framework and a composite clamp sleeve, wherein the clamp framework is of a strip-shaped structure, one end of the clamp framework is provided with a clamp head, and the inner side surface of the other end of the clamp framework is provided with a clamping tooth part; the composite clamp sleeve is of a strip-shaped structure and comprises a clamp sleeve body and a pressure change part arranged on the inner side surface of the clamp sleeve body, wherein the clamp sleeve body sequentially comprises an inner silicon rubber layer, a glass fiber fabric layer and an outer silicon rubber layer from inside to outside, and a through cavity is formed along the length central line direction of the clamp sleeve body; the pressure change portion comprises a plurality of convex bodies, the clamp framework is arranged in the through cavity of the clamp sleeve body in a penetrating mode, and the clamp clamping head and the clamping tooth portion are located outside the clamp sleeve body.

2. The pipeline harness clip for an aircraft engine according to claim 1, wherein a plurality of the bosses are arranged in sequence in a width direction of the clip body, and a length of each boss is equal to a length of the clip body.

3. The pipeline harness clip for an aircraft engine according to claim 1, wherein a plurality of the bosses are arranged in sequence along a length direction of the clip body, and a length of each boss is equal to a width of the clip body.

4. A pipeline harness clip for an aircraft engine according to claim 2 or 3 wherein a plurality of said bosses are parallel to each other and equally spaced.

5. The aircraft engine conduit harness clip of claim 4 wherein the width of the bottom surface of the boss is 1 to 2.5 times the spacing between adjacent bosses.

6. The aircraft engine conduit harness clip of claim 5 wherein said boss is triangular in longitudinal cross-section.

7. The aircraft engine conduit harness clip of claim 5 wherein said boss is trapezoidal in longitudinal cross-section.

8. The aircraft engine conduit harness clip of claim 7 wherein the width of the bottom surface of the boss is 0.5 to 5 times the height of the boss.

9. The aircraft engine conduit harness clip of claim 1 wherein the clip frame is a metallic material.