A dovetail tip compressor rotor blade coating protection device and method

Abstract

The application discloses a dovetail tenon compressor rotor blade coating protection device and method, and relates to the technical field of compressor rotor blade coating protection devices. The bottom plate is provided with a plurality of protection units for protecting the edge plate and blade body of the dovetail tenon compressor rotor blade in an annular array. The protection unit comprises a support and a positioning assembly. The support is a hollow structure with an open top. The hollow part of the support is used for accommodating the blade body of the dovetail tenon compressor rotor blade. The top of the support is provided with vertical baffles on opposite sides. The positioning assembly comprises a first positioning block and a second positioning block arranged between the vertical baffles. The opposite faces of the first positioning block and the second positioning block are connected in a stopper fitting mode. The opposite faces of the first positioning block and the second positioning block are both provided with special-shaped grooves. The cavity structure formed by the special-shaped grooves on the opposite faces is shaped according to the edge plate and part of the blade body of the dovetail tenon compressor rotor blade. The application aims to solve the protection problem of non-coating areas during the surface coating processing of the dovetail tenon compressor rotor blade.

Description

Technical Field

[0001] This invention pertains to surface coating protection technology, specifically a coating protection device and method for dovetail tenon compressor rotor blades. Background Technology

[0002] Blades are among the most numerous and crucial components of an aero-engine. After machining, the dovetail tenon compressor rotor blades achieve their final spatial geometry and dimensions. According to relevant technical requirements, to improve the quality, operating conditions, service life, and reliability of the dovetail tenon compressor rotor blades, a surface coating process is required on the dovetail tenon symmetry surface of the blades. Figure 1 (Shaded areas in the image). During surface coating, the coated area needs to undergo sandblasting and coating processes; at the same time, the uncoated areas need to be protected to avoid damage that could cause unnecessary scratches, overspray, or other quality problems.

[0003] The dovetail-shaped tenon compressor rotor blade can be divided into three main parts: the blade body, the rim plate, and the tenon. The blade body has a complex spatial profile, the rim plate is an irregular parallelogram shape, and the tenon has a dovetail cross-section. The blade body and the tenon are connected together by the rim plate at a specific spatial position. During surface coating, the blade body and rim plate need to be protected. Due to the irregular shape of the blade body and rim plate, rigid protection devices are insufficient. Therefore, tape wrapping has been used for protection during production. Tape wrapping offers advantages such as ease of operation and adaptability. However, tape wrapping also has the following disadvantages: ① Large tape consumption and single-use nature; ② Poor transition between coated and uncoated areas; ③ Inconsistent quality; ④ Numerous repetitive tasks involving applying and repairing tape before coating, and removing and cleaning tape residue after coating; ⑤ Uncontrollable factors during processing—sudden tape peeling; ⑥ Long processing cycle and low efficiency for dovetail-shaped tenon compressor rotor blades. These problems have long existed, seriously affecting production delivery. Summary of the Invention

[0004] To address the problems existing in the prior art, the present invention provides a coating protection device and method for dovetail tenon compressor rotor blades, the purpose of which is to solve the problem of protecting the non-coated areas during the coating process of dovetail tenon compressor rotor blades.

[0005] To solve the above-mentioned technical problems, the present invention is achieved through the following technical solution:

[0006] According to a first aspect of the present invention, a dovetail tenon compressor rotor blade coating protection device is provided, comprising:

[0007] The base plate is provided with a plurality of protective units arranged in a circular array to protect the edge plates and blade body of the dovetail tenon compressor rotor blades.

[0008] The protection unit includes:

[0009] The support is a hollow structure with an open top. The hollow part of the support is used to accommodate the blade of the dovetail tenon compressor rotor. Vertical baffles are respectively provided on the opposite sides of the top of the support.

[0010] The positioning component includes a first positioning block and a second positioning block disposed between the vertical baffles. The opposing surfaces of the first positioning block and the second positioning block are connected by a stop joint. The opposing surfaces of the first positioning block and the second positioning block are provided with irregular grooves. The cavity structure formed by the irregular grooves on the opposing surfaces conforms to the edge plate and part of the blade of the dovetail tenon compressor rotor blade.

[0011] In one possible implementation of the first aspect, the bottom of the support is provided with a protrusion, and the base plate is provided with a plug hole that mates with the protrusion, and the protrusion is inserted into the plug hole.

[0012] In one possible implementation of the first aspect, the protrusion has a square cross-section, and the insertion hole is a square hole.

[0013] In one possible implementation of the first aspect, the protective unit is made of an elastic non-metallic material.

[0014] In one possible implementation of the first aspect, the support is made of polyetheretherketone (PEEK) material, and the positioning component is made of silicone rubber material.

[0015] In one possible implementation of the first aspect, handles are provided on opposite sides of the outer surface of the base plate.

[0016] In one possible implementation of the first aspect, a convex stop is provided on the side of the first positioning block facing the second positioning block, and a concave stop corresponding to the convex stop is provided on the side of the second positioning block facing the first positioning block.

[0017] In one possible implementation of the first aspect, the positioning component is interference-fitted between the vertical baffles.

[0018] In one possible implementation of the first aspect, the base plate is provided with a plurality of weight-reducing holes.

[0019] According to a second aspect of the present invention, a method for coating and protecting dovetail tenon compressor rotor blades is provided, comprising the aforementioned dovetail tenon compressor rotor blade coating and protection device, including:

[0020] The edge plate and part of the blade of the dovetail compressor rotor blade are assembled and covered by the irregular grooves on the facing surfaces of the first positioning block and the second positioning block, and the dovetail tenon of the dovetail compressor rotor blade extends out of the positioning assembly.

[0021] The positioning assembly, which is fitted with dovetail tenon compressor rotor blades, is installed between the vertical baffles at the top of the support, and the blade body of the dovetail tenon compressor rotor blades extends into the hollow structure of the support.

[0022] The assembled protection unit is installed on the base plate.

[0023] Compared with the prior art, the present invention has at least the following beneficial effects:

[0024] Based on any of the above aspects, the present invention utilizes the irregular grooves on the facing surfaces of the first and second positioning blocks to assemble and cover the edge plate and part of the blade of the dovetail tenon compressor rotor blade. The positioning assembly with the dovetail tenon compressor rotor blade is installed between the vertical baffles at the top of the support. The blade of the dovetail tenon compressor rotor blade extends into the hollow structure of the support. This solves the problem of protecting the uncoated area when coating the surface of the dovetail tenon symmetry surface of the compressor rotor blade, and effectively protects the uncoated area of ​​the dovetail tenon compressor rotor blade. The use of a dovetail tenon compressor rotor blade coating protection device improves the transition between coated and uncoated areas, enhances and stabilizes the quality of the dovetail tenon compressor rotor blades, and saves a significant amount of disposable tape usage. It also reduces a large amount of simple and repetitive work such as applying and repairing tape before coating, and tearing and cleaning tape residue after coating. This shortens the processing cycle of the dovetail tenon compressor rotor blades, improves efficiency, and eliminates uncontrollable factors during processing, such as sudden tape peeling.

[0025] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 A side view of the rotor blades of a dovetail-shaped compressor;

[0028] Figure 2 This is an isometric view of a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0029] Figure 3 This is an isometric view (partially cut open) of the protection unit in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0030] Figure 4 This is a structural diagram of the support in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention, wherein (a) is a front view, (b) is a side view, (c) is a top view, and (d) is an isometric view;

[0031] Figure 5 This is an isometric view of the positioning component in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0032] Figure 6 This is a top view of the base plate in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0033] Figure 7 This is a side sectional view (with dimensions) of the base plate in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0034] Figure 8 This is a top view (with dimension markings) of the base plate in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0035] Figure 9 This is a front view (with dimension markings) of the support in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0036] Figure 10 This is a top view (with dimension markings) of the support in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention;

[0037] Figure 11 The diagram shows the structure of the positioning component in a dovetail tenon compressor rotor blade coating protection device according to an embodiment of the present invention (with dimension markings), wherein (a) is a top view, (b) is a sectional view along the AA direction, and (c) is a sectional view along the BB direction.

[0038] In the diagram: 1-base plate; 10-insertion hole; 11-handle; 12-weight reduction hole; 2-protection unit; 20-support; 200-vertical baffle; 201-protrusion; 21-positioning component; 210-first positioning block; 2100-protruding stop; 211-second positioning block; 2110-recessed stop; 3-dovetail tenon compressor rotor blade. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] Combination Figure 2 and Figure 6 As shown in the figure, an embodiment of the present invention provides a coating protection device for dovetail tenon compressor rotor blades, including a base plate 1. A plurality of protection units 2 are arranged in a circular array on the base plate 1 for protecting the dovetail tenon compressor rotor blades. That is, the protection units 2 protect the uncoated parts (blade edge and blade body) of the dovetail tenon compressor rotor blades, while the dovetail tenons of the coated parts are exposed outside the protection units 2. Figure 1 As shown, the shaded area on the tenon is the coated part.

[0041] Specifically, such as Figure 3 As shown, each protection unit 2 includes a support 20 and a positioning component 21. The structure and cooperation relationship between the support 20 and the positioning component 21 are as follows:

[0042] like Figure 4 As shown, the support 20 is a hollow structure with an open top. The hollow part of the support 20 is used to accommodate the blade of the dovetail-shaped compressor rotor. Vertical baffles 200 are respectively provided on opposite sides of the top of the support 20. For example, the support 20 is rectangular, and the vertical baffles 200 are integrally formed with the support 20.

[0043] like Figure 5As shown, the positioning component 21 includes a first positioning block 210 and a second positioning block 211 disposed between vertical baffles 200. The opposing surfaces of the first positioning block 210 and the second positioning block 211 are connected by a stop. Irregularly shaped grooves are formed on the opposing surfaces of both the first positioning block 210 and the second positioning block 211, and the cavity structure formed by the irregularly shaped grooves on the opposing surfaces conforms to the rim plate and part of the blade body of the dovetail-shaped compressor rotor blade. That is, according to the structural shape of the rim plate and the part of the blade body near the rim plate of the dovetail-shaped compressor rotor blade, matching irregularly shaped grooves are formed on two opposing surfaces of the first positioning block 210 and the second positioning block 211. When the stops of the first positioning block 210 and the second positioning block 211 are engaged, the cavity formed by the irregularly shaped grooves is used to accommodate the rim plate and the part of the blade body near the rim plate of the dovetail-shaped compressor rotor blade, thereby effectively protecting the uncoated parts of the dovetail-shaped compressor rotor blade.

[0044] The dovetail tenon compressor rotor blade coating protection device of this embodiment is used to protect the dovetail tenon compressor rotor blades during coating. The specific installation and operation process is as follows:

[0045] First, the edge plate and part of the blade of the dovetail compressor rotor blade are assembled and covered by the irregular grooves on the facing surfaces of the first positioning block 210 and the second positioning block 211, thus completing the protection of the edge plate and part of the blade of the dovetail compressor rotor blade. After covering, the dovetail tenon of the dovetail compressor rotor blade to be coated extends out of the positioning component 21.

[0046] Next, the positioning assembly 21, which is equipped with the dovetail tenon compressor rotor blades, is installed between the vertical baffles 200 on the top of the support 20. At this time, the blade of the dovetail tenon compressor rotor blade extends into the hollow structure of the support 20. That is to say, the remaining blade that is not covered by the positioning assembly 21 extends into the hollow structure of the support 20, and the support 20 effectively protects it.

[0047] Finally, following the assembly method described above, after assembling all the protection units 2 with the dovetail tenon compressor rotor blades, the assembled protection units 2 are installed on the base plate 1, and the base plate 1 is installed on the coating equipment, so that the exposed tenons of the dovetail tenon compressor rotor blades can be coated.

[0048] Based on the above embodiments, as a more preferred embodiment, such as Figure 3 and Figure 4 As shown, a protrusion 201 is also provided at the bottom of the support 20. For example, the protrusion 201 and the support 20 are integrally formed. An insertion hole 10 is provided on the base plate 1 to cooperate with the protrusion 201. The protrusion 201 is inserted into the insertion hole 10, thereby realizing the assembly connection between the support 20 and the base plate 1.

[0049] In a preferred embodiment, such as Figure 4 As shown, the cross-section of the protrusion 201 is square, as... Figure 6 As shown, the insertion hole 10 is a square hole. After the two are inserted and assembled, there will be no rotational displacement, which can better ensure the stability and reliability of the support 20 and the base plate 1 after assembly.

[0050] In one embodiment, the protection unit 2 is made of an elastic non-metallic material. Preferably, the support 20 is made of polyetheretherketone (PEEK) material, and the positioning component 21 is made of silicone rubber material.

[0051] In one embodiment, such as Figure 2 As shown, handles 11 are provided on opposite sides of the outer surface of the base plate 1. The handles 11 facilitate the movement and handling of the base plate 1 by the operator. For example, the handles 11 are welded to the outer surface of the base plate 1.

[0052] As an optional implementation method, combined with Figure 3 and Figure 5 As shown, the specific form of the opposing surface stop connection of the first positioning block 210 and the second positioning block 211 can be as follows: a convex stop 2100 is provided on the side of the first positioning block 210 facing the second positioning block 211, and a concave stop 2110 corresponding to the convex stop 2100 is provided on the side of the second positioning block 211 facing the first positioning block 210. That is to say, the opposing surface stop connection of the first positioning block 210 and the second positioning block 211 is achieved by the mutual cooperation of the convex stop 2100 and the concave stop 2110.

[0053] For example, the convex stop 2100 is composed of a protruding short cylinder and an end face, while the concave stop 2110 is composed of a short hole and an end face. Preferably, two protruding short cylinders are provided on both sides of the first positioning block 210, and similarly, two short holes are provided on both sides of the second positioning block 211, which can facilitate a convenient, quick, and reliable connection between the opposing surfaces of the first positioning block 210 and the second positioning block 211.

[0054] In one embodiment, the positioning component 21 is installed between the vertical baffles 200 with an interference fit. It should be understood that a small interference fit should be used for installation, as long as the positioning component 21 can be disassembled and installed between the vertical baffles 200.

[0055] In one embodiment, such as Figure 6As shown, a number of weight-reducing holes 12 are provided on the base plate 1. For example, the base plate 1 is a circular plate, and a number of protective units 2 are arranged in a ring array on the circular edge of the base plate 1. A larger weight-reducing hole is provided in the middle of the circular plate, and a number of smaller weight-reducing holes are provided on the inner side of the protective units 2 in the ring array. This can reduce the weight of the base plate while ensuring the structural strength of the base plate 1.

[0056] The following is a more detailed explanation of the dovetail tenon compressor rotor blade coating protection device of the present invention.

[0057] Using UG 3D software for modeling and simulation analysis, a flexible non-metallic, left-right opening and closing fully enclosed structure is employed to protect the uncoated areas of the dovetail tenon compressor rotor blades. The complex and irregular structure of the rotor blade's edge plates and blade body is transformed into a regular shape after protection by the protective unit before the dovetail tenon coating process. The flexible non-metallic, left-right opening and closing fully enclosed structure consists of a first positioning block and a second positioning block, designed synchronously as a whole. To achieve elastic deformation and a certain degree of temperature resistance, silicone rubber is selected for manufacturing. During the design process, the first and second positioning blocks are designed as a whole, encompassing all spatial geometric elements that need to be protected in the uncoated area. Model analysis and experimental data comparison are performed on the designed first and second positioning blocks. Based on the analysis and comparison results, the model is enlarged, reduced, or kept unchanged to ensure complete fit with the protected dovetail tenon compressor rotor blades, effectively protecting the protected area. Suitable parting surfaces are identified to form independent first and second positioning blocks, facilitating the clamping of the dovetail tenon compressor rotor blades.

[0058] The detailed structure of base plate 1 is as follows: Figure 7 and Figure 8 As shown, reference A serves as the positioning reference for the entire protection device, and its functions are as follows: ① It connects to the equipment workbench to ensure the installation position of the entire protection device and equipment; ② It serves as the design and installation reference for other components in the protection device. The boss diameter 1d1 in the base plate 1 is a centering shaft to make the protection device concentric with the equipment workbench, and the hole diameter 1D1 is a weight-reducing hole. Figure 8 Dimension 1L1 is the distance from the handle to the rotation center; Dimension 1L2 is the distance from the rotation center to each of the 36 square holes in this embodiment; Dimensions 1L3 and 1L4 are the dimensions of the square holes, which match the dimensions of the protrusions on the support; Diameter 1d2 is the maximum outer diameter of the base plate; Diameter 1D2 of each of the 36 round holes is a weight-reducing hole, and Diameter 1D3 is the distribution pitch circle of hole D2. To reduce the overall weight of the protective device and facilitate field use, the base plate 1 is made of hard aluminum (LY11), which is approximately 1 / 3 the weight of carbon steel under the same structure and size conditions. The overall design is... Figure 8 The shape shown.

[0059] Support 20 Figure 9 and Figure 10 As shown, to effectively control the weight of the protective device and meet the temperature resistance requirements (≥220℃) at the coating site, polyetheretherketone (PEEK) is selected as the material. Dimensions 2L2, 2L3, and 2H1 together define the geometric dimensions of the support; dimensions 2L6, 2L7, and 2H3 together define the geometric dimensions of the protrusion at the bottom of the support. This dimension matches the size of the square hole on the base plate 1, and the protrusion is installed in the hole above the base plate 1 during use; dimensions 2L4, 2L5, and 2H4 together define the size of the hollow cavity of the support; dimensions 2L1 and 2H2 together define the installation position of the positioning component 21. During use, the positioning component 21 is installed here with a small interference fit, so that the positioning component is completely protected and does not detach during the coating process. The entire support structure is as follows. Figure 11 As shown.

[0060] To facilitate on-site use and management, and to prevent misassembly and omissions, the first and second positioning blocks are painted in different colors. This color differentiation prevents errors, thus eliminating basic problems such as misassembly and omissions. The positioning component design follows this sequence: 1. Based on the relevant technical documents for the dovetail-shaped compressor rotor blades, use UG 3D software to model the dovetail-shaped compressor rotor blades; 2. Combining the coating process, relevant technical requirements, and the dovetail-shaped compressor rotor blade model from step 1, analyze the key points, difficulties, and specific structures to be considered in the positioning component design; 3. Based on the material property calculation results, engineering experience, and the positioning component structure, determine whether the theoretical model of the dovetail-shaped compressor rotor blades needs to be enlarged, reduced, or kept unchanged when implementing the process scheme; 4. Using UG 3D software, model the dovetail-shaped compressor rotor blades from step 1... The theoretical model of the sub-blade is divided into different parts: the blade body, the rim plate, and the tenon. Based on the analysis results in step 3, the blades are enlarged, reduced, or kept as is. 5. Modeling is performed in UG 3D software using commands such as extrusion, shelling, Boolean operations, and trimming to design the protective device models for the blade body and rim plate. 6. Boolean summation is performed on each part of the model from step 5 to obtain the overall structure of the protective device, and the overall structure is optimized. 7. The structural shape is improved to match the support. 8. The structure is analyzed to find a suitable parting surface, dividing the overall positioning component into left and right parts to form the first positioning block and the second positioning block. Figure 11 As shown, dimensions L1, L2, and L3 are the closed dimensions after the first and second positioning blocks clamp the parts. Dimension L1 matches the support dimension 2L1 to ensure an interference fit of 0.2mm to 0.3mm.

[0061] Finally, it should be noted that the above-described embodiments are merely specific implementations of the present invention, used to illustrate the technical solutions of the present invention, and not to limit it. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention, or make equivalent substitutions for some of the technical features; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A coating protection device for dovetail-shaped tenon compressor rotor blades, characterized in that, include: The base plate (1) is provided with a number of protective units (2) arranged in a ring array on the base plate (1) for protecting the edge plates and blades of the dovetail tenon compressor rotor blades. The protection unit (2) includes: Support (20), the support (20) is a hollow structure with an open top, the hollow part of the support (20) is used to accommodate the blade of the dovetail tenon compressor rotor blade, and vertical baffles (200) are respectively provided on the opposite sides of the top of the support (20). The positioning component (21) includes a first positioning block (210) and a second positioning block (211) disposed between the vertical baffles (200). The opposing surfaces of the first positioning block (210) and the second positioning block (211) are connected by a stop fit. The opposing surfaces of the first positioning block (210) and the second positioning block (211) are provided with irregular grooves, and the cavity structure formed by the irregular grooves on the opposing surfaces conforms to the edge plate and part of the blade of the dovetail tenon compressor rotor blade. The positioning component (21) is interference-fitted between the vertical baffles (200). The protective unit (2) is made of elastic non-metallic material; The support (20) is made of polyetheretherketone material, and the positioning component (21) is made of silicone rubber material; The first positioning block (210) has a convex stop (2100) on the side facing the second positioning block (211), and the second positioning block (211) has a concave stop (2110) on the side facing the first positioning block (210) that corresponds to the convex stop (2100).

2. The dovetail tenon compressor rotor blade coating protection device according to claim 1, characterized in that, The bottom of the support (20) is provided with a protrusion (201), and the base plate (1) is provided with a plug hole (10) that cooperates with the protrusion (201). The protrusion (201) is inserted into the plug hole (10).

3. The dovetail tenon compressor rotor blade coating protection device according to claim 2, characterized in that, The cross-section of the protrusion (201) is square, and the insertion hole (10) is a square hole.

4. The dovetail tenon compressor rotor blade coating protection device according to claim 1, characterized in that, Handles (11) are provided on opposite sides of the outer surface of the base plate (1).

5. The dovetail tenon compressor rotor blade coating protection device according to claim 1, characterized in that, The base plate (1) has several weight-reducing holes (12).

6. A method for coating and protecting the rotor blades of a dovetail-shaped tenon compressor, characterized in that, The dovetail tenon compressor rotor blade coating protection device as described in any one of claims 1 to 5 includes: The edge plate and part of the blade of the dovetail compressor rotor blade are assembled and covered by the irregular grooves on the facing surfaces of the first positioning block (210) and the second positioning block (211), and the dovetail tenon of the dovetail compressor rotor blade extends out of the positioning component (21). The positioning assembly (21) with the dovetail tenon compressor rotor blades is installed between the vertical baffles (200) on the top of the support (20), and the blades of the dovetail tenon compressor rotor blades extend into the hollow structure of the support (20). The assembled protection unit (2) is installed on the base plate (1).

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