Protective cover of aircraft engine

Abstract

The utility model relates to the technical field of engine protection covers, and discloses an aircraft engine protection cover which comprises an elastic cloth belt and a fixing belt strip, one end of the fixing belt strip is fixedly connected with an adjusting belt strip, the inner walls of the front side and the rear side of a sliding groove are fixedly connected with springs, the other ends of the springs are fixedly connected with sliding blocks, and the sliding blocks are fixedly connected with the elastic cloth belt. A limiting clamping block is fixedly connected to the outer surface of the bottom of the sliding block, and a plurality of limiting protruding strips are arranged on the outer surface of the adjusting strip in a linear array mode. According to the size of the aircraft engine, through cooperation of the limiting protruding strips, the springs and the limiting clamping blocks, the fixing belt strips and the adjusting belt strips are adjusted to the positions matched with the size of the rear end of the aircraft engine, and therefore the fixing belt strips and the adjusting belt strips are clamped on the surface of the aircraft engine, and the protection cloth cover is fixed to the aircraft engine; and the phenomenon that the rope is in contact with the tip and the protrusion on the surface of the engine to cause abrasion to finally cause falling of the protective cover is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of engine protection covers, in particular to a protection cover for an aircraft engine. Background Technique

[0002] An aircraft engine, also known as an aeroengine, is a highly complex and precise thermal machine. As the heart of an aircraft, it is not only the power for the aircraft to fly but also an important driving force for the development of the aviation industry. During the assembly and maintenance of an aircraft engine, a large amount of waste chips and foreign objects will be generated. If the aircraft engine inhales them, it will cause damage to the aircraft engine. For example, metal chips generated during hole making, excess glue generated during sealing, and residues generated during the installation of fasteners and other components will fall into the aircraft engine. Therefore, a protection cover needs to be installed outside the engine. Currently, the engine protection cover is usually made of canvas or rainproof cloth in the form of a cloth cover.

[0003] Currently, when installing the aircraft engine protection cover, the protection cover is installed on the front side of the engine through an installation ladder, and then connected to the rear side of the engine by multiple ropes or tapes, so as to install the protection cover on the engine and prevent the protection cover from falling off. However, when using ropes to fix the protection cover on the engine, due to the presence of tips and protrusions on the rear side of the aircraft engine, it is inconvenient to tie the ropes together at the rear of the engine, and the ropes placed at the rear are prone to wear when contacting the tips and protrusions on the surface of the engine, ultimately resulting in the detachment of the protection cover. Therefore, a protection cover for an aircraft engine is proposed. Content of the Utility Model

[0004] In view of the deficiencies of the prior art, the utility model provides a protection cover for an aircraft engine to solve the problems mentioned in the above background technique.

[0005] To achieve the above object, the utility model provides the following technical solution: A protection cover for an aircraft engine, comprising an elastic cloth belt and a fixing strip. A protection cloth cover is arranged inside the elastic cloth belt. One end of the fixing strip is fixedly connected with an adjusting strip. The outer surface of the fixing strip far from the connection of the adjusting strip is fixedly connected with an adjusting seat. A sliding groove is opened on the top outer surface of the adjusting seat. Springs are fixedly connected to the inner walls on both the front and rear sides of the sliding groove. The other ends of the springs are fixedly connected with sliders. A limiting block is fixedly connected to the bottom outer surface of the slider. A number of limiting protrusions are linearly arranged on the outer surface of the adjusting strip.

[0006] Furthermore, a first connecting seat is fixedly connected to the opposite outer surfaces of the elastic cloth belt and the fixing strip. A second connecting seat is fixedly connected to the outer surface of the adjusting strip. A first nylon belt is fixedly connected to the outer surfaces of the first connecting seat and the second connecting seat on the outer surface of the fixing strip. A second nylon belt is fixedly connected to the outer surface of the connecting seat on the outer surface of the elastic cloth belt.

[0007] Furthermore, a hook surface of a magic tape is fixedly connected to an outer surface of the first nylon belt on a side facing the second nylon belt, and a loop surface of the magic tape is fixedly connected to an outer surface of the second nylon belt on a side facing the first nylon belt.

[0008] Furthermore, a slide bar is fixedly connected to an inside of the chute, the slider is movably sleeved on an outer surface of the slide bar, and the spring is sleeved on the outer surface of the slide bar.

[0009] Furthermore, an arc-shaped groove is formed in an outer surface of the adjusting strip close to the elastic cloth strip, an arc-shaped rod is fixedly connected to an inside of the arc-shaped groove, an arc-shaped sliding plate is movably sleeved on an outer surface of the arc-shaped rod, and the second connecting seat is fixedly connected to an outer surface of the arc-shaped sliding plate.

[0010] Furthermore, outer surfaces of one sides of the limit blocks close to the limit ridges are all inclined.

[0011] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0012] 1. For the protective cover of the aircraft engine, by sleeving the protective cloth cover on the outside of the aircraft engine, according to the size of the aircraft engine, the positions between the fixing strip and the adjusting strip are adjusted, and in cooperation with the limit ridges, the spring and the limit blocks, the fixing strip and the adjusting strip are adjusted to positions adapted to the size of the rear end of the aircraft engine, so as to clamp the fixing strip and the adjusting strip on the surface of the aircraft engine, thereby realizing the fixation of the protective cloth cover on the aircraft engine, and preventing the phenomenon that the rope contacts the tips and protrusions on the surface of the engine and wears, eventually leading to the detachment of the protective cover.

[0013] 2. For the protective cover of the aircraft engine, according to the length sizes of different aircraft engines, the first nylon belt and the second nylon belt are connected through the loop surface and the hook surface of the magic tape, the length between the first nylon belt and the second nylon belt is adjusted, and then another nylon belt is taken, and the connection part between the first nylon belt and the second nylon belt is tied to the surface of the aircraft engine to increase the stability between the first nylon belt and the second nylon belt. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a front view structural schematic diagram of the present utility model;

[0015] Figure 2 is a rear view structural schematic diagram of the present utility model;

[0016] Figure 3 is a partial cross-sectional structural schematic diagram of the present utility model;

[0017] Figure 4 is a structural schematic diagram of an adjusting seat of the present utility model;

[0018] Figure 5 For the present utility model Figure 4 a schematic enlarged structure view of part A;

[0019] Figure 6 a schematic structure view of the connection part of the first nylon belt and the second nylon belt of the present utility model.

[0020] In the figure: 1, elastic cloth belt; 2, protective cloth cover; 3, fixed belt strip; 4, adjusting belt strip; 5, adjusting seat; 6, limiting convex strip; 7, spring; 8, slider; 9, limiting block; 10, first nylon belt; 11, second nylon belt; 12, hook surface of Velcro; 13, arc groove; 14, arc sliding plate; 15, sliding rod. Specific embodiments

[0021] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0022] Embodiment 1:

[0023] Please refer to Figures 1-6, the present utility model provides a technical solution: a protective cover for an aircraft engine, including an elastic cloth belt 1 and a fixed belt strip 3. A protective cloth cover 2 is arranged inside the elastic cloth belt 1. One end of the fixed belt strip 3 is fixedly connected with an adjusting belt strip 4. The outer surface of the fixed belt strip 3 away from the connection of the adjusting belt strip 4 is fixedly connected with an adjusting seat 5. A chute is provided on the outer surface of the top of the adjusting seat 5. Springs 7 are fixedly connected to the inner walls on both the front and rear sides of the chute. The other end of the spring 7 is fixedly connected with a slider 8. A limiting block 9 is fixedly connected to the outer surface of the bottom of the slider 8. A number of limiting ridges 6 are arranged in a linear array on the outer surface of the adjusting belt strip 4. Specifically, the protective cloth cover 2 is put on the front side of the aircraft engine, and then the fixed belt strip 3 is attached to the outer side of the rear end of the aircraft engine. According to the size of the outer side of the rear end of the aircraft engine, the position of the adjusting belt strip 4 on the surface of the fixed belt strip 3 is adjusted. One end of the adjusting belt strip 4 is inserted into the adjusting seat 5, and force is applied to the adjusting belt strip 4, so that the limiting ridges 6 squeeze the limiting blocks 9 to both sides, causing the spring 7 to deform. After the fixed belt strip 3 and the adjusting belt strip 4 are adjusted to the corresponding size of the outer side of the rear end of the aircraft engine, the force applied to the adjusting belt strip 4 is stopped, so that the limiting block 9 is between two adjacent limiting ridges 6 to limit the adjusting belt strip 4. When the adjusting belt strip 4 is not stressed, it is stuck outside the fixed belt strip 3. And because the aircraft engine is larger at the front and smaller at the rear, the fixed belt strip 3 and the adjusting belt strip 4 will not move forward, thus realizing the fixation of the protective cloth cover 2 on the aircraft engine, and there will be no phenomenon that the rope contacts the tips and protrusions on the surface of the engine and wears, eventually resulting in the detachment of the protective cover.

[0024] In this embodiment, a first connecting seat is fixedly connected to the opposite outer surfaces of the elastic cloth belt 1 and the fixed belt strip 3. A second connecting seat is fixedly connected to the outer surface of the adjusting belt strip 4. A first nylon belt 10 is fixedly connected to the outer surfaces of the first connecting seat and the second connecting seat on the outer surface of the fixed belt strip 3. A second nylon belt 11 is fixedly connected to the outer surface of the connecting seat on the outer surface of the elastic cloth belt 1. Specifically, the elastic cloth bag and the fixed belt strip 3 are connected as a whole through the connection of the first nylon belt 10 and the second nylon belt 11 between the elastic cloth bag and the fixed belt strip 3 and the adjusting belt strip 4.

[0025] In this embodiment, a magic tape hook surface is fixedly connected to the outer surface of the first nylon belt 10 facing the second nylon belt 11. A magic tape loop surface 12 is fixedly connected to the outer surface of the second nylon belt 11 facing the first nylon belt 10. Specifically, the first nylon belt 10 and the second nylon belt 11 are pasted through the magic tape hook surface and the magic tape loop surface 12. The pasting position of the magic tape hook surface and the magic tape loop surface 12 is adjusted, the length between the first nylon belt 10 and the second nylon belt 11 is adjusted. After the adjustment is completed, another nylon belt is taken, and the connection between the first nylon belt 10 and the second nylon belt 11 is tied to the surface of the aircraft engine to increase the stability between the first nylon belt 10 and the second nylon belt 11.

[0026] In this embodiment, a slide bar 15 is fixedly connected inside the chute. The slider 8 is movably sleeved on the outer surface of the slide bar 15, and the spring 7 is sleeved on the outer surface of the slide bar 15. Specifically, when the limit block 9 moves to both sides, the slider 8 slides on the outer surface of the slide bar 15, so that the slider 8 and the limit block 9 can stably perform linear motion, and the spring 7 is limited by the slide bar 15 to prevent the spring 7 from deforming obliquely.

[0027] In this embodiment, an arc groove 13 is formed on the outer surface of the adjusting strip 4 close to the elastic cloth strip 1. An arc rod is fixedly connected inside the arc groove 13, and an arc slide plate 14 is movably sleeved on the outer surface of the arc rod. The second connecting seat is fixedly connected to the outer surface of the arc slide plate 14. Specifically, when adjusting the position of the adjusting strip 4 between the fixed strips 3, the arc slide plate 14 slides on the surface of the arc rod, so that the second connecting seat is always located on one side of the adjusting seat 5, preventing the second connecting seat from being in relative contact with the adjusting seat 5 and causing the position between the adjusting strip 4 and the fixed strip 3 to be unadjustable.

[0028] In this embodiment, the sides of the limit block 9 close to the limit convex strip 6 are all inclined outer surfaces. Specifically, by providing the limit block 9 with an inclined surface, when a force is applied to the adjusting strip 4, the limit convex strip 6 can squeeze the limit block 9 to move to both sides, causing the spring 7 to deform.

[0029] Working principle: When the present utility model is in use, the protective cloth cover 2 is sleeved on the front side of the aircraft engine, and then the fixed strip 3 is attached to the outer side of the rear end of the aircraft engine. According to the size of the outer side of the rear end of the aircraft engine, the position of the adjusting strip 4 on the surface of the fixed strip 3 is adjusted. One end of the adjusting strip 4 is inserted into the adjusting seat 5, and a force is applied to the adjusting strip 4, so that the limit convex strip 6 squeezes the limit block 9 to both sides, causing the spring 7 to deform. After the fixed strip 3 and the adjusting strip 4 are adjusted to the dimensions corresponding to the outer side of the rear end of the aircraft engine, the force applied to the adjusting strip 4 is stopped, so that the limit block 9 is located between two adjacent limit convex strips 6 to limit the adjusting strip 4. When the adjusting strip 4 is not stressed, it is stuck outside the fixed strip 3. Since the aircraft engine is large at the front and small at the rear, the fixed strip 3 and the adjusting strip 4 will not move forward, thus realizing the fixation of the protective cloth cover 2 on the aircraft engine, and preventing the rope from contacting the tips and protrusions on the surface of the engine and wearing, which ultimately leads to the detachment of the protective cover.

[0030] Adjust the position between the first nylon belt 10 and the second nylon belt 11 according to the length dimensions of the front end and the rear end of the aircraft engine, so that the hook surface 12 of the Velcro adheres to the loop surface. After adjusting the lengths of the first nylon belt 10 and the second nylon belt 11 and fixing the fixing strap 3, take another nylon belt and tie the connection between the first nylon belt 10 and the second nylon belt 11 to the surface of the aircraft engine to increase the stability between the first nylon belt 10 and the second nylon belt 11.

[0031] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A protective cover for an aircraft engine, comprising an elastic cloth belt (1) and a fixing strip (3), characterized in that: A protective cloth cover (2) is arranged inside the elastic cloth belt (1). One end of the fixed belt strip (3) is fixedly connected to an adjusting belt strip (4). An adjusting seat (5) is fixedly connected to the outer surface of the fixed belt strip (3) away from the connection with the adjusting belt strip (4). A chute is formed on the top outer surface of the adjusting seat (5). Springs (7) are fixedly connected to the inner walls on the front and rear sides of the chute. The other ends of the springs (7) are fixedly connected to sliders (8). A limiting latch (9) is fixedly connected to the bottom outer surface of the slider (8). A number of limiting ridges (6) are arranged in a linear array on the outer surface of the adjusting belt strip (4).

2. The protective cover of an aircraft engine according to claim 1, wherein: A first connection seat is fixedly connected to the opposite outer surfaces of the elastic cloth belt (1) and the fixed belt strip (3). A second connection seat is fixedly connected to the outer surface of the adjusting belt strip (4). A first nylon belt (10) is fixedly connected to the outer surfaces of the first connection seat and the second connection seat on the outer surface of the fixed belt strip (3). A second nylon belt (11) is fixedly connected to the outer surface of the connection seat on the outer surface of the elastic cloth belt (1).

3. The protective cover of an aircraft engine according to claim 2, characterized in that: A magic tape hook surface is fixedly connected to the outer surface of the first nylon belt (10) on the side facing the second nylon belt (11). A magic tape loop surface (12) is fixedly connected to the outer surface of the second nylon belt (11) on the side facing the first nylon belt (10).

4. The protective cover of an aircraft engine according to claim 1, wherein: A sliding rod (15) is fixedly connected to the inside of the chute. The slider (8) is movably sleeved on the outer surface of the sliding rod (15). The spring (7) is sleeved on the outer surface of the sliding rod (15).

5. The protective cover of an aircraft engine according to claim 2, characterized in that: An arc-shaped groove (13) is formed on the outer surface of the adjusting belt strip (4) close to the elastic cloth belt (1). An arc-shaped rod is fixedly connected to the inside of the arc-shaped groove (13). An arc-shaped sliding plate (14) is movably sleeved on the outer surface of the arc-shaped rod. The second connection seat is fixedly connected to the outer surface of the arc-shaped sliding plate (14).

6. The protective cover of an aircraft engine according to claim 1, characterized in that: The outer surfaces of the sides of the limiting latch (9) close to the limiting ridges (6) are all inclined.

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