Wind and sand prevention cover for aircraft engine

Abstract

The utility model discloses a wind-sand-proof cover for an aircraft engine, which belongs to the technical field of wind-sand-proof covers and is characterized by comprising an aircraft engine body, the outer wall of the aircraft engine body is sleeved with a stabilizing structure, and the inner wall of the stabilizing structure is bolted with a protective structure. The outer side of the protection structure is fixedly connected with an auxiliary structure, the inner wall of the mounting frame is fixedly connected with the outer wall of a mesh cloth block, the inner wall of the mounting piece is fixedly connected with the outer wall of a film block, and the inner wall of the connecting piece is fixedly connected with the outer wall of a filter block. Especially in frequent sand storm or desert and dry areas, an engine air inlet system of an airplane easily sucks sand and dust and particulate matters in air, the sand and dust particles contain fine sand and soil particles, and the particulate matters not only damage precise parts in an engine, but also possibly cause reduction of the efficiency of the engine.

Description

Technical Field

[0001] This utility model relates to the field of windproof and sandproof cover technology, and in particular to a windproof and sandproof cover for aircraft engines. Background Technology

[0002] Sand shields are one of the important protective devices for aircraft engines. They are usually installed at the engine air intake or front end. Their main function is to prevent sand, dust and other particulate matter from entering the engine through physical isolation or filtration mechanisms. Sand shields also need to have good air permeability to ensure that the engine receives sufficient airflow, while effectively blocking sand and dust.

[0003] To address the aforementioned problems, existing patents offer solutions. During aircraft parking, especially in areas with frequent sandstorms or deserts and arid regions, the aircraft's engine intake system can easily draw in sand and particulate matter from the air. These sand particles contain fine sand particles, which can not only damage the precision components inside the engine but also lead to a decrease in engine efficiency.

[0004] Therefore, a sand shield for aircraft engines is proposed. Utility Model Content

[0005] The purpose of this invention is to provide a sand shield for aircraft engines, which can solve the problem that when aircraft are parked, especially in areas with frequent sandstorms or deserts and dry regions, the aircraft engine intake system can easily inhale sand and particulate matter from the air. Sand particles contain fine sand particles, which can not only damage the precision components inside the engine, but may also lead to a decrease in engine efficiency.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a sand shield for an aircraft engine, comprising an aircraft engine body, a stabilizing structure sleeved on the outer wall of the aircraft engine body, a protective structure bolted to the inner wall of the stabilizing structure, and an auxiliary structure fixedly connected to the outer side of the protective structure.

[0007] The protective structure includes a mounting frame, a mesh block, a mounting component, a membrane block, a connector, and a filter block. The inner wall of the mounting frame is fixedly connected to the outer wall of the mesh block. The inner wall of the mounting component is fixedly connected to the outer wall of the membrane block. The inner wall of the connector is fixedly connected to the outer wall of the filter block. The right side of the mounting frame is movably connected to the left side of the mounting component. The right side of the mounting component is movably connected to the left side of the connector. The right side of the connector is movably connected to the left side of the aircraft engine body. The right side of the mesh block is movably connected to the left side of the membrane block. The right side of the membrane block is movably connected to the left side of the filter block. The right side of the filter block is movably connected to the left side of the aircraft engine body.

[0008] Preferably, a stabilizing cover is bolted to the outer wall of the mounting frame, the inner wall of the stabilizing cover is bolted to the inner wall of the mounting component, and the inner wall of the stabilizing cover is bolted to the outer wall of the connector.

[0009] Preferably, the inner wall of the stabilizer is fitted with the outer wall of the aircraft engine body, and a rubber ring is fixedly connected to the inner wall of the stabilizer, with the left side of the rubber ring being movably connected to the right side of the connector.

[0010] Preferably, the right side of the rubber ring is movably connected to the left side of the aircraft engine body, and a connecting block is fixedly connected to the right side of the outer wall of the stabilizer.

[0011] Preferably, a fixing block is fixedly connected to the outer wall of the connecting block, a fixing member is inserted into the inner wall of the fixing block, and a fastening block is threadedly connected to the inner wall of the fixing member.

[0012] Preferably, the right side of the fastening block is movably connected to the left side of the fixing block, and a connecting rope is fixedly connected to the right side of the fixing member.

[0013] Preferably, the inner side of the connecting rope is movably connected to the outer side of the aircraft engine body, and a mounting block is fixedly connected to the right side of the connecting rope, with the inner wall of the mounting block sleeved with the outer wall of the aircraft engine body.

[0014] Preferably, the outer walls of the mounting frame, mounting component, and connector are all provided with connecting grooves, and the outer wall of the stabilizing cover is provided with a plurality of connecting holes.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. The protective structure set up in this application forms a graded filtration system through a multi-layer design. The outer mesh block blocks larger particles, the middle membrane block blocks fine particles and sand, and the inner filter block further improves the filtration accuracy. The multi-layer protection ensures that sand and dust will not enter the engine body, effectively improving the service life and safety of the engine.

[0017] 2. The auxiliary structure provided in this application further stabilizes the entire sand and wind shield after the protective structure and stabilizing structure are fitted onto the outer wall of the engine body, preventing it from falling off due to external forces and ensuring the continuity and reliability of the protection. Attached Figure Description

[0018] Figure 1 This is an overall structural diagram of the sand shield for an aircraft engine according to the present invention.

[0019] Figure 2 This is a diagram of the protective structure of this utility model;

[0020] Figure 3 This is an overall view of the stable structure of this utility model;

[0021] Figure 4 This is a connection diagram of the auxiliary structure of this utility model;

[0022] Figure 5 This is a connection diagram of the aircraft engine body of this utility model.

[0023] In the diagram, 1. Aircraft engine body; 2. Stabilizing structure; 21. Stabilizing cover; 22. Rubber ring; 23. Connecting block; 3. Protective structure; 31. Mounting frame; 32. Mesh block; 33. Mounting component; 34. Membrane block; 35. Connecting component; 36. Filter block; 4. Auxiliary structure; 41. Fixing block; 42. Fixing component; 43. Fastening block; 44. Connecting rope; 45. Mounting block; 5. Connecting groove; 6. Connecting hole. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] Please see Figure 1-5 The present invention provides the following technical solution:

[0026] A sand shield for an aircraft engine includes an aircraft engine body 1, a stabilizing structure 2 sleeved on the outer wall of the aircraft engine body 1, a protective structure 3 bolted to the inner wall of the stabilizing structure 2, and an auxiliary structure 4 fixedly connected to the outer side of the protective structure 3.

[0027] The protective structure 3 includes a mounting frame 31, a mesh block 32, a mounting component 33, a membrane block 34, a connector 35, and a filter block 36. The inner wall of the mounting frame 31 is fixedly connected to the outer wall of the mesh block 32. The inner wall of the mounting component 33 is fixedly connected to the outer wall of the membrane block 34. The inner wall of the connector 35 is fixedly connected to the outer wall of the filter block 36. The right side of the mounting frame 31 is movably connected to the left side of the mounting component 33. The right side of the mounting component 33 is movably connected to the left side of the connector 35. The right side of the connector 35 is movably connected to the left side of the aircraft engine body 1. The right side of the mesh block 32 is movably connected to the left side of the membrane block 34. The right side of the membrane block 34 is movably connected to the left side of the filter block 36. The right side of the filter block 36 is movably connected to the left side of the aircraft engine body 1.

[0028] In this embodiment: by setting up the stabilizing structure 2, the user can sequentially install the connector 35, the mounting piece 33 and the mounting frame 31 to the inner side of the stabilizing structure 2, then put the stabilizing structure 2 on the outer wall of the aircraft engine body 1, and then put the auxiliary structure 4 on the other side of the aircraft engine body 1 and connect it with the stabilizing structure 2 to increase the stability of the stabilizing structure 2. The protective structure 3 includes a mesh block 32 made of high-strength woven material to block large particles of sand and debris, a membrane block 34 made of windproof membrane material to provide sealing while preventing the aircraft engine body 1 from accumulating internal moisture due to long-term sealing, and a filter block 36 made of ultra-fine fiber mesh to filter small particles in the air and prevent fine dust from entering the interior of the aircraft engine body 1.

[0029] Specifically, such as Figure 3 , Figure 5 As shown, a stabilizing cover 21 is bolted to the outer wall of the mounting frame 31, the inner wall of the stabilizing cover 21 is bolted to the inner wall of the mounting component 33, and the inner wall of the stabilizing cover 21 is bolted to the outer wall of the connector 35.

[0030] Specifically, such as Figure 3 , Figure 5 As shown, the inner wall of the stabilizer 21 is sleeved with the outer wall of the aircraft engine body 1, and a rubber ring 22 is fixedly connected to the inner wall of the stabilizer 21. The left side of the rubber ring 22 is movably connected to the right side of the connector 35.

[0031] Specifically, such as Figure 3 , Figure 5 As shown, the right side of the rubber ring 22 is movably connected to the left side of the aircraft engine body 1, and the right side of the outer wall of the stabilizer 21 is fixedly connected to the connecting block 23.

[0032] In this embodiment: When the protective structure 3 is needed to protect the aircraft engine body 1, the user can install the protective structure 3 on the inner wall of the stabilizer 21, and then take the stabilizer 21 and put it on the outer wall of the aircraft engine body 1. The rubber ring 22 fixed on the inner wall of the stabilizer 21 is used to increase the sealing of the stabilizer 21 installation. By setting the connecting block 23 fixed on the outer wall of the stabilizer 21, the auxiliary structure 4 can be fixed to the outer wall of the stabilized structure.

[0033] Specifically, such as Figure 4 , Figure 5 As shown, a fixing block 41 is fixedly connected to the outer wall of the connecting block 23, a fixing member 42 is inserted into the inner wall of the fixing block 41, and a fastening block 43 is threadedly connected to the inner wall of the fixing member 42.

[0034] Specifically, such as Figure 4 , Figure 5As shown, the right side of the fastening block 43 is movably connected to the left side of the fixing block 41, and the right side of the fixing member 42 is fixedly connected to the connecting rope 44.

[0035] Specifically, such as Figure 4 , Figure 5 As shown, the inner side of the connecting rope 44 is movably connected to the outer side of the aircraft engine body 1, and the right side of the connecting rope 44 is fixedly connected to the mounting block 45, the inner wall of the mounting block 45 is sleeved with the outer wall of the aircraft engine body 1.

[0036] In this embodiment: By setting the auxiliary structure 4, when the stabilizing structure 2 and the protective structure 3 are fitted onto the outer wall of the aircraft engine body 1, the user will fit the mounting block 45 onto the other side of the outer wall of the aircraft engine body 1, and then pull the connecting rope 44 to the fixing block 41 fixed on the stabilizing structure 2 through the fixing member 42, and insert the fixing member 42 into the inner wall of the fixing block 41. At the same time, the fastening block 43 is threaded to the inner wall of the fixing member 42, so that the fixing member 42 is stabilized on the fixing block 41. The setting of the connecting rope 44 part can prevent the stabilizing structure 2 fitted onto the outer wall of the aircraft engine body 1 from falling off.

[0037] Specifically, such as Figure 2 , Figure 3 , Figure 5 As shown, the outer walls of the mounting frame 31, mounting component 33 and connector 35 are all provided with connecting grooves 5, and the outer wall of the stabilizing cover 21 is provided with several connecting holes 6.

[0038] In this embodiment: the mounting frame 31, the mounting member 33 and the connector 35 are connected by the connecting groove 5 and the connecting holes 6 are provided in the stabilizing cover 21. The mounting frame 31, the mounting member 33 and the connector 35 are then fixed to the inner wall of the stabilizing cover 21 by means of the connecting groove 5 provided in the mounting frame 31, the mounting member 33 and the connector 35.

[0039] Working principle: When it is necessary to install a sand and dust shield on the aircraft engine body 1, the user can first install the connector 35, the mounting piece 33 and the mounting frame 31 to the inside of the stabilizing structure 2 in sequence. Then, the stabilizing structure 2 is fitted onto the outer wall of the aircraft engine body 1. Next, the auxiliary structure 4 is fitted onto the other side of the aircraft engine body 1 and connected to the stabilizing structure 2 to increase the stability of the stabilizing structure 2. The protective structure 3 includes a mesh block 32 made of high-strength woven material to block large particles of sand and dust and debris, a membrane block 34 made of windproof membrane material to provide sealing and prevent the aircraft engine body 1 from accumulating internal moisture due to long-term sealing, and a filter block 36 made of ultra-fine fiber mesh to filter small particles in the air and prevent fine dust from entering the interior of the aircraft engine body 1.

[0040] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A sand shield for an aircraft engine, comprising an aircraft engine body (1), characterized in that: The outer wall of the aircraft engine body (1) is fitted with a stabilizing structure (2), the inner wall of the stabilizing structure (2) is bolted with a protective structure (3), and the outer side of the protective structure (3) is fixedly connected with an auxiliary structure (4). The protective structure (3) includes a mounting frame (31), a mesh block (32), a mounting component (33), a membrane block (34), a connector (35), and a filter block (36). The inner wall of the mounting frame (31) is fixedly connected to the outer wall of the mesh block (32). The inner wall of the mounting component (33) is fixedly connected to the outer wall of the membrane block (34). The inner wall of the connector (35) is fixedly connected to the outer wall of the filter block (36). The right side of the mounting frame (31) is movably connected to the left side of the mounting component (33). The right side of the mounting component (33) is movably connected to the left side of the connector (35). The right side of the connector (35) is movably connected to the left side of the aircraft engine body (1). The right side of the mesh block (32) is movably connected to the left side of the membrane block (34). The right side of the membrane block (34) is movably connected to the left side of the filter block (36). The right side of the filter block (36) is movably connected to the left side of the aircraft engine body (1).

2. The sand shield for an aircraft engine according to claim 1, characterized in that: The outer wall of the mounting frame (31) is bolted with a stabilizing cover (21), the inner wall of the stabilizing cover (21) is bolted with the inner wall of the mounting component (33), and the inner wall of the stabilizing cover (21) is bolted with the outer wall of the connector (35).

3. A sand shield for an aircraft engine according to claim 2, characterized in that: The inner wall of the stabilizer (21) is fitted with the outer wall of the aircraft engine body (1). A rubber ring (22) is fixedly connected to the inner wall of the stabilizer (21). The left side of the rubber ring (22) is movably connected to the right side of the connector (35).

4. A sand shield for an aircraft engine according to claim 3, characterized in that: The right side of the rubber ring (22) is movably connected to the left side of the aircraft engine body (1), and a connecting block (23) is fixedly connected to the right side of the outer wall of the stabilizer (21).

5. A sand shield for an aircraft engine according to claim 4, characterized in that: The outer wall of the connecting block (23) is fixedly connected to a fixing block (41), the inner wall of the fixing block (41) is inserted with a fixing member (42), and the inner wall of the fixing member (42) is threadedly connected to a fastening block (43).

6. A sand shield for an aircraft engine according to claim 5, characterized in that: The right side of the fastening block (43) is movably connected to the left side of the fixing block (41), and the right side of the fixing member (42) is fixedly connected to the connecting rope (44).

7. A sand shield for an aircraft engine according to claim 6, characterized in that: The inner side of the connecting rope (44) is movably connected to the outer side of the aircraft engine body (1), and the right side of the connecting rope (44) is fixedly connected to the mounting block (45), and the inner wall of the mounting block (45) is sleeved with the outer wall of the aircraft engine body (1).

8. A sand shield for an aircraft engine according to claim 2, characterized in that: The outer walls of the mounting frame (31), mounting component (33) and connector (35) are all provided with connecting grooves (5), and the outer wall of the stabilizing cover (21) is provided with several connecting holes (6).

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