Abrasive particle flow machining tool for removing remelting layer and inner cavity residues of turbine blade film hole

Abstract

The utility model discloses an abrasive flow machining tool for removing remelting layers of film holes and inner cavity residues of turbine blades, relates to the technical field of polishing of the remelting layers of the film holes and the inner cavity residues of the turbine blades, and aims to solve the problems that existing polishing operation is inconvenient to operate, the polishing effect needs to be improved, meanwhile, polishing equipment is inconvenient to disassemble, assemble and overhaul, and the polishing efficiency is low. According to the technical scheme, the device is characterized by comprising an abrasive flow equipment lower cylinder, an abrasive flow equipment upper cylinder, an upper die plate and a lower die plate, the upper die plate is installed in an installation position of the abrasive flow equipment upper cylinder, the lower die plate is installed in an installation position of the abrasive flow equipment lower cylinder, and a grinding and polishing barrel is installed between the upper die plate and the lower die plate; and a lower mold plate material guiding opening is formed in the middle of the lower mold plate, and a blade crown sealing rubber block is installed on the bottom end face of the interior of the grinding and polishing barrel in a buckled mode. The effects that the workpiece can be rapidly and conveniently disassembled and assembled, meanwhile, the polishing effect of the turbine blade can be improved, and practicability is high are achieved.

Description

Technical Field

[0001] This utility model relates to the field of polishing technology for the remelted layer of the air film hole and the residue in the inner cavity of turbine blades, and in particular to an abrasive flow machining tool for removing the remelted layer of the air film hole and the residue in the inner cavity of turbine blades. Background Technology

[0002] With the increasing inlet air temperature of aero-engines and gas turbines, turbine blades often require complex internal cooling channels and film cooling holes machined on the blade body using electrical discharge machining (EDM) to allow cooling air to enter, thereby improving the high-temperature resistance of the turbine blades. However, EDM machining of film cooling holes creates a remelted layer of a certain thickness on the hole walls, which negatively impacts the fatigue performance of the blades. This remelted layer needs to be removed or reduced to a certain thickness using abrasive flow machining or other methods. During the casting process, especially for oriented and single-crystal turbine blades, the molten metal reacts with the ceramic core at high temperatures. This reaction layer cannot be completely removed during subsequent core removal. Furthermore, a small amount of residual core and reactants may adhere to the inner surface of the blade during core removal, negatively affecting the service performance of the turbine blades. If a coating needs to be applied to the inner cavity, these residues also significantly hinder the coating's adhesion.

[0003] Existing polishing operations are inconvenient to operate, the polishing effect needs to be improved, and the polishing equipment is not easy to disassemble and maintain, so its practicality needs to be improved. Utility Model Content

[0004] The purpose of this invention is to provide an abrasive flow machining fixture for removing the remelted layer and internal cavity residues of turbine blade film holes, which can quickly and conveniently disassemble and assemble workpieces, while improving the polishing effect of turbine blades, and is highly practical.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A grinding flow machining fixture for removing remelted layers and internal residues from the film cooling holes of turbine blades includes a lower cylinder of a grinding flow equipment, an upper cylinder of a grinding flow equipment, an upper template, and a lower template. The upper template is installed in the mounting position of the upper cylinder of the grinding flow equipment, and the lower template is installed in the mounting position of the lower cylinder of the grinding flow equipment. A polishing barrel is installed between the upper and lower templates. A lower template guide port is provided at the middle position of the lower template. A blade crown sealing rubber block is snapped onto the inner bottom surface of the polishing barrel. Guide holes corresponding to the positions of the lower template guide ports are provided at the middle position of the blade crown sealing rubber block and on the bottom surface of the polishing barrel. An upper template guide port is provided on the upper template.

[0007] By adopting the above technical solution, workpieces can be quickly and conveniently assembled and disassembled, while the polishing effect can be improved, making it highly practical.

[0008] Furthermore, a piston for the lower cylinder of the abrasive flow equipment is provided at the middle position of the lower cylinder, and the cavity between the piston and the lower template is filled with abrasive material.

[0009] By adopting the above technical solution, polishing operations can be achieved using abrasives.

[0010] Furthermore, a blade clamping block is fixedly installed at the middle position of the inner end face of the upper template, and a turbine blade is clamped between the blade clamping block and the blade crown sealing rubber block.

[0011] By adopting the above technical solutions, the positional stability of turbine blades can be improved.

[0012] Furthermore, four support columns are installed between the upper and lower templates. The upper ends of the support columns are fixedly connected to the upper template by locking bolts, and positioning holes are provided on the lower end face of the support columns.

[0013] By adopting the above technical solutions, the working stability of the entire tooling can be effectively improved.

[0014] Furthermore, an upper template sealing rubber strip is provided at the edge of the upper end face of the upper template, a lower template sealing rubber ring is provided at the edge of the lower end face of the lower template, and a grinding and polishing barrel sealing rubber ring is provided at the upper end of the grinding and polishing barrel.

[0015] By adopting the above technical solutions, the sealing performance of the entire tooling can be effectively improved, and the stability of polishing can be enhanced.

[0016] Furthermore, a lower template positioning protrusion is integrally connected to the lower end face of the lower template, and the lower template positioning protrusion is engaged in the mounting position of the lower cylinder of the abrasive flow device.

[0017] By adopting the above technical solution, the entire tooling can be installed quickly.

[0018] In summary, the beneficial technical effects of this utility model are as follows:

[0019] This invention allows for the following steps: First, the turbine blade to be processed is snapped onto the crown sealing rubber block. Then, the upper template is fastened to the upper port of the polishing barrel. The assembled fixture is then installed between the lower cylinder and the upper cylinder of the abrasive flow equipment. Next, abrasive is used to polish the turbine blade. During polishing, the piston in the lower cylinder of the abrasive flow equipment pushes the abrasive, allowing it to pass sequentially through the lower template guide port and guide hole into the interior of the turbine blade. It then passes through the air film holes of the turbine blade into the polishing barrel. As the abrasive continues to enter, once the polishing barrel is full, it passes through the upper template guide port into the cavity of the upper cylinder of the abrasive flow equipment. Then, the piston in the upper cylinder of the abrasive flow equipment is activated, causing the abrasive to move in the reverse direction inside the polishing barrel, thus achieving efficient polishing. This fixture effectively improves the ease of operation and polishing effect of turbine blade polishing. Furthermore, the fixture allows for flexible and convenient assembly and disassembly, making it highly practical. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the internal structure of this utility model.

[0021] In the diagram: 1. Upper template; 11. Upper template sealing rubber strip; 12. Locking bolt; 13. Upper template guide port; 14. Blade clamping block; 2. Grinding barrel; 21. Grinding barrel sealing rubber ring; 22. Blade crown sealing rubber block; 3. Support column; 4. Lower template; 41. Lower template guide port; 42. Lower template positioning protrusion; 43. Lower template sealing rubber ring; 5. Turbine blade; 6. Abrasive; 7. Lower cylinder of abrasive flow equipment; 8. Lower cylinder piston of abrasive flow equipment; 9. Upper cylinder of abrasive flow equipment. Detailed Implementation

[0022] The method of this utility model will be further described in detail below with reference to the accompanying drawings.

[0023] Reference Figure 1A grinding flow machining fixture for removing the remelted layer and internal residues from the film gas pores of turbine blades includes a lower cylinder 7, an upper cylinder 9, an upper template 1, and a lower template 4. The upper template 1 is installed in the mounting position of the upper cylinder 9, and the lower template 4 is installed in the mounting position of the lower cylinder 7. A polishing barrel 2 is installed between the upper template 1 and the lower template 4. A lower template guide port 41 is provided at the middle position of the lower template 4. A blade crown sealing rubber block 22 is snapped onto the bottom surface inside the polishing barrel 2. A guide hole corresponding to the position of the lower template guide port 41 is provided at the middle position of the rubber block 22 and on the bottom end face of the grinding and polishing barrel 2. An upper template guide port 13 is provided on the upper template 1. A blade clamping block 14 is fixedly installed at the middle position of the inner end face of the upper template 1. A turbine blade 5 is clamped between the blade clamping block 14 and the blade crown sealing rubber block 22. A lower cylinder piston 8 of the abrasive flow equipment is provided at the middle position of the lower cylinder 7. The cavity between the lower cylinder piston 8 and the lower template 4 is filled with abrasive material 6. In operation, the turbine blade 5 to be processed is snapped onto the crown sealing rubber block 22. Then, the upper template 1 is fastened onto the upper port of the polishing barrel 2. The assembled fixture is then installed between the lower cylinder 7 and the upper cylinder 9 of the abrasive flow equipment. Next, the abrasive 6 is used to polish the turbine blade 5. During polishing, the piston 8 in the lower cylinder 7 of the abrasive flow equipment pushes the abrasive 6, allowing it to pass sequentially through the lower template guide port 41 and the guide hole into the interior of the turbine blade 5, and then through... The air film vent of the turbine blade 5 enters the interior of the polishing barrel 2. As the abrasive 6 continues to enter, once the polishing barrel 2 is filled with abrasive 6, it passes through the upper template guide port 13 of the upper template 1 and enters the cavity of the cylinder 9 of the abrasive flow equipment. Then, the piston in the cylinder 9 of the abrasive flow equipment is activated, allowing the abrasive 6 to move in the reverse direction inside the polishing barrel 2, thereby achieving efficient polishing operation. This tooling effectively improves the ease of operation and polishing effect of polishing the turbine blade 5. At the same time, this tooling can be flexibly and conveniently disassembled and assembled, making it highly practical.

[0024] Reference Figure 1 Four support columns 3 are installed between the upper template 1 and the lower template 4. The upper end of the support column 3 is fixedly connected to the upper template 1 by the locking bolt 12. The lower end face of the support column 3 is provided with positioning holes. The lower end face of the lower template 4 is integrally connected with the lower template positioning protrusion 42. The lower template positioning protrusion 42 is engaged in the installation position of the lower cylinder 7 of the abrasive flow equipment. The support columns 3 can be used to improve the structural firmness and stability of the entire tooling when it is working, thereby improving the working stability of the tooling.

[0025] Reference Figure 1An upper template sealing rubber strip 11 is provided at the edge of the upper end face of the upper template 1, a lower template sealing rubber ring 43 is provided at the edge of the lower end face of the lower template 4, and a grinding and polishing barrel sealing rubber ring 21 is provided at the upper end of the grinding and polishing barrel 2. The upper template sealing rubber strip 11 can be used to improve the sealing between the upper template 1 and the abrasive flow equipment cylinder 9, the lower template sealing rubber ring 43 can be used to improve the sealing between the lower template 4 and the abrasive flow equipment cylinder 7, and the grinding and polishing barrel sealing rubber ring 21 can be used to improve the sealing between the grinding and polishing barrel 2 and the upper template 1, thereby further improving the processing stability of the entire tooling.

[0026] Working principle: In use, the turbine blade 5 to be processed is snapped onto the crown sealing rubber block 22. Then, the upper template 1 is snapped onto the upper port of the polishing barrel 2. The assembled fixture is then installed between the lower cylinder 7 and the upper cylinder 9 of the abrasive flow equipment. Next, the abrasive 6 is used to polish the turbine blade 5. During polishing, the piston 8 of the lower cylinder 7 of the abrasive flow equipment pushes the abrasive 6, allowing it to pass through the guide port 41 of the lower template and the guide hole into the interior of the turbine blade 5, and then through... The abrasive 6 enters the interior of the polishing barrel 2 through the film gas hole of the turbine blade 5. As the abrasive 6 continues to enter, when the polishing barrel 2 is filled with abrasive 6, it passes through the upper template guide port 13 of the upper template 1 and enters the cavity of the cylinder 9 of the abrasive flow equipment. Then, the piston in the cylinder 9 of the abrasive flow equipment is activated, so that the abrasive 6 can move in the opposite direction inside the polishing barrel 2, thereby achieving efficient polishing operation. This tooling effectively improves the ease of operation and polishing effect of polishing turbine blade 5. At the same time, the tooling can be flexibly and conveniently disassembled and assembled, making it highly practical.

[0027] The specific real-time examples described herein are preferred real-time examples of this utility model and are not intended to limit the scope of protection of this utility model. Therefore, all equivalent changes made to the structure, shape, and principle of this utility model should be included within the scope of protection of this utility model.

Claims

1. An abrasive flow machining fixture for removing the remelted layer and internal cavity residue of a turbine blade film gas pore, comprising a lower cylinder (7) of an abrasive flow device, an upper cylinder (9) of an abrasive flow device, an upper template (1), and a lower template (4), characterized in that: The upper template (1) is installed in the mounting position of the cylinder (9) of the abrasive flow equipment, and the lower template (4) is installed in the mounting position of the lower cylinder (7) of the abrasive flow equipment. A polishing barrel (2) is installed between the upper template (1) and the lower template (4). A lower template guide port (41) is provided at the middle position of the lower template (4). A blade crown sealing rubber block (22) is snapped on the inner bottom end face of the polishing barrel (2). A guide hole corresponding to the position of the lower template guide port (41) is provided at the middle position of the blade crown sealing rubber block (22) and at the bottom end face of the polishing barrel (2). An upper template guide port (13) is provided on the upper template (1).

2. The abrasive flow machining tooling for removing the remelted layer and internal cavity residues of turbine blade film perforations according to claim 1, characterized in that: A piston (8) for the lower cylinder (7) of the abrasive flow equipment is provided at the middle position, and the cavity between the piston (8) and the lower template (4) is filled with abrasive material (6).

3. The abrasive flow machining tooling for removing the remelted layer and internal cavity residues of turbine blade film gas holes according to claim 1, characterized in that: A blade clamping block (14) is fixedly installed at the middle position of the inner end face of the upper template (1), and a turbine blade (5) is clamped between the blade clamping block (14) and the blade crown sealing rubber block (22).

4. The abrasive flow machining tooling for removing the remelted layer and internal cavity residues of turbine blade film gas holes according to claim 1, characterized in that: Four support columns (3) are installed between the upper template (1) and the lower template (4). The upper end of the support column (3) is fixedly connected to the upper template (1) by a locking bolt (12). A positioning hole is provided on the lower end face of the support column (3).

5. The abrasive flow machining tooling for removing the remelted layer and internal cavity residue of turbine blade film pores according to claim 1, characterized in that: An upper template sealing rubber strip (11) is provided at the edge of the upper end face of the upper template (1), a lower template sealing rubber ring (43) is provided at the edge of the lower end face of the lower template (4), and a grinding and polishing barrel sealing rubber ring (21) is provided at the upper end of the grinding and polishing barrel (2).

6. The abrasive flow machining tooling for removing the remelted layer and internal cavity residue of turbine blade film gas holes according to claim 1, characterized in that: The lower template (4) is integrally connected to a lower template positioning protrusion (42) on its lower end surface, and the lower template positioning protrusion (42) is engaged in the mounting position of the lower cylinder (7) of the abrasive flow equipment.

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