Tool for removing aero-engine blade coatings in batches

Abstract

The utility model discloses a tool for removing aero-engine blade coatings in batches, and belongs to the technical field of aero-engines. Comprising a cleaning basket, a cross beam, clamping blocks and check blocks. The cleaning basket is of a frame structure; each cross beam comprises a mounting part located at the top and a connecting part located at the lower part, each connecting part is in a strip shape with a T-shaped section, and the cross beams are distributed on the top frame of the cleaning basket at intervals through the mounting parts; a T-shaped groove matched with the connecting part is formed in the top of the clamping block, and a tooth groove matched with an engine blade tenon in shape is formed in the bottom of the clamping block; the cleaning basket is provided with a limiting groove on the outer side of a tail end beam mounted on the cross beam; the stop block is in an L shape, one arm of the stop block is matched with the limiting groove in shape, and the other arm of the stop block is provided with a T-shaped inserting groove inserted into the connecting part. The tool is simple in structure, convenient to disassemble and assemble and capable of removing aero-engine blade coatings in batches.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to a tool for batch removing coatings from aviation engine blades. Background Art

[0002] Existing methods for removing coatings (such as AlSiY) from aircraft engine blades commonly include: 1. Stacking blades and placing them in an acidic cleaning tank. However, due to the limited size of the cleaning tank, a relatively small number of blades can be cleaned at one time. 2. Utilizing the tenon-groove structure of the blade joint, the blades are suspended from a wire frame and placed in the cleaning tank. This approach fails to secure the blades and can easily cause them to shake and collide. Both methods result in low coating removal efficiency and limited effectiveness. Summary of the Invention

[0003] In order to overcome the above-mentioned defects of the prior art, the utility model aims to provide a tool for quickly and efficiently removing coatings from aircraft engine blades in batches.

[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0005] A tool for batch removal of coatings on aircraft engine blades, comprising a cleaning basket, a crossbeam, a clamping block, and a stopper; the cleaning basket is a frame structure; the crossbeam comprises a mounting portion at the top and a connecting portion at the bottom, the connecting portion being a strip with a T-shaped cross section, and there are multiple crossbeams distributed on the top frame of the cleaning basket at intervals through the mounting portion; the top of the clamping block is provided with a T-slot that matches the connecting portion, and the bottom is provided with a tooth groove that matches the shape of the tenon of the engine blade; the cleaning basket is provided with a limiting groove on the outside of the end beam where the crossbeam is installed; the stopper is "L"-shaped, with one arm matching the shape of the limiting groove and the other arm provided with a T-slot that is inserted into the connecting portion.

[0006] Preferably, a plurality of spacers are further included; each spacer is provided with a T-shaped through slot that matches the shape of the connecting portion and is used for being installed between adjacent clamping blocks.

[0007] Preferably, the cleaning basket, crossbeam, spacer and stopper are all made of polytetrafluoroethylene.

[0008] Compared with the prior art, the present invention has the following advantages:

[0009] 1. When removing the coating, the blade is mounted on the clamping block via the tenon, and the clamping block is then mounted on the crossbeam. Multiple clamping blocks can be mounted on one crossbeam, and a cleaning basket can be equipped with multiple crossbeams. This tooling allows for batch removal of coatings from multiple blades with consistent results. This overcomes the drawbacks of the prior art, which limited the number of blades that can be cleaned and made it difficult to secure the blades.

[0010] 2. Based on the above advantages, it greatly saves manpower and cleaning time during coating cleaning and improves work efficiency.

[0011] 3. The entire device has a simple structure and can be realized by simply plugging the installation block, spacer block, stop block and the connecting part of the beam, which is extremely convenient to operate.

[0012] 4. The material design of cleaning related structures (cleaning basket, beams, spacers and blocks) provides good protection for blade cleaning and prevents scratches. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is the overall structure diagram;

[0014] Figure 2 It is a side cross-sectional structural diagram;

[0015] Figure 3 This is a structural diagram of the cleaning basket;

[0016] Figure 4 This is the beam structure diagram;

[0017] Figure 5 To install the block structure diagram;

[0018] Figure 6 It is the structural diagram of the spacer block;

[0019] Figure 7 It is the block structure diagram;

[0020] Figure 8 This is a diagram of a commonly used blade structure.

[0021] In the figure: 1. cleaning basket; 11. limiting groove; 2. crossbeam; 21. connecting part; 22. mounting part; 3. clamping block; 31. T-slot; 32. tooth groove; 4. spacer; 41. T-slot; 5. stop block; 51. T-slot. DETAILED DESCRIPTION

[0022] The structure and principle of the present invention are now fully explained in conjunction with specific embodiments so that those skilled in the art can fully understand and implement them.

[0023] like Figures 1 to 7 As shown, a tool for batch removal of coatings from aircraft engine blades includes a cleaning basket 1, a crossbeam 2, a clamping block 3, and a stopper 5, where m is an aircraft blade to be de-coated.

[0024] The cleaning basket 1 is a frame structure; the crossbeam 2 includes a mounting portion 22 at the top and a connecting portion 21 at the bottom. The connecting portion 21 is a strip with a T-shaped cross section. There are multiple crossbeams 2, which are distributed on the top frame of the cleaning basket 1 at intervals through the mounting portion 22. The top of the clamping block 3 is provided with a T-slot 31 adapted to the connecting portion 21, and the bottom is provided with a tenon for the engine blade (such as Figure 8 The tooth groove 32 is adapted to the shape of a commonly used blade structure diagram; the cleaning basket 1 is provided with a limiting groove 11 on the outside of the end beam installed on the crossbeam 2; the stopper 5 is "L"-shaped, one arm is adapted to the shape of the limiting groove 11, and the other arm is provided with a T-shaped slot 51 inserted into the connecting portion 21.

[0025] When in use, the clamping block 3 is fixedly connected to the tenon of the engine blade through the tooth groove 32 (for example, fixed by protective wax), and is inserted into the connecting part 21 through the T-slot 31 and installed under the beam 2. One beam 2 can be equipped with multiple blades; the T-slot 51 of the stop block 5 seals the outside of the beam 2 to prevent the clamping block 3 from slipping out.

[0026] Through the above design, when removing the coating, the whole tool can be placed in the cleaning tank to carry out the work in batches, and the removal effect can be guaranteed with good consistency.

[0027] Further configuration includes a plurality of spacers 4, each of which is provided with a T-shaped slot 41 adapted to the shape of the connection portion 21 and is used to be installed between adjacent clamping blocks 3. Installing the spacers 4 between adjacent clamping blocks 3 effectively avoids collisions between adjacent blades during the coating removal process.

[0028] Preferably, the cleaning basket 1, the crossbeam 2, the spacer 4 and the stopper 5 are all made of polytetrafluoroethylene. Through the material design, the possible scratches caused by the tooling to the blades are prevented.

[0029] The above embodiments are merely preferred embodiments of the present invention and are not intended to constitute any formal limitation on the present invention. Any person skilled in the art can, without departing from the technical principles and scope of the present invention, utilize the methods disclosed above to make many possible changes and modifications to the technical solutions of the present invention, or modify them into equivalent embodiments with equivalent variations. Therefore, any combination, modification, or replacement of the technical features disclosed in the present invention based on the technical essence of the present invention, without departing from the principles or scope of the present invention, shall fall within the scope of protection of the technical solution of the present invention.

Claims

1. A tool for batch removal of coatings from aircraft engine blades, characterized in that: The invention comprises a cleaning basket (1), a crossbeam (2), a clamping block (3), and a stopper (5); the cleaning basket (1) is a frame structure; the crossbeam (2) comprises a mounting portion (22) at the top and a connecting portion (21) at the bottom, the connecting portion (21) being a strip with a T-shaped cross section; the crossbeam (2) is provided in plurality and is spaced apart and distributed on the top frame of the cleaning basket (1) through the mounting portion (22); the top of the clamping block (3) is provided with a T-shaped slot (31) adapted to the connecting portion (21), and the bottom is provided with a tooth groove (32) adapted to the shape of the tenon of an engine blade; the cleaning basket (1) is provided with a limiting slot (11) on the outer side of the end beam where the crossbeam (2) is mounted; the stopper (5) is "L"-shaped, one arm of which is adapted to the shape of the limiting slot (11), and the other arm of which is provided with a T-shaped slot (51) inserted into the connecting portion (21).

2. The tool for batch removal of coatings from aircraft engine blades according to claim 1, characterized in that: It also includes a plurality of spacers (4); each spacer (4) is provided with a T-shaped through slot (41) that matches the shape of the connecting portion (21) and is used for being installed between adjacent clamping blocks (3).

3. The tool for batch removal of coatings from aircraft engine blades according to claim 2, characterized in that: The cleaning basket (1), crossbeam (2), spacer (4) and stopper (5) are all made of polytetrafluoroethylene material.

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