Low-pressure turbine working blade film coating tool

Abstract

The invention relates to the technical field of low-pressure turbine working blade film coating, in particular to a low-pressure turbine working blade film coating tool which comprises the following steps that a support, a planetary gear transmission system located in the support and a plurality of blade clamp assemblies fixedly connected with the planetary gear transmission system are included, and a gear ring is fixedly arranged at the top end of the support; wherein the blade clamp assembly is used for clamping a tenon and a blade crown of a turbine working blade respectively; the planetary gear transmission system drives the turbine working blades to rotate and revolve around the interior of the gear ring at the same time through the blade clamp assembly. By adopting the tool provided by the invention in the film coating process of the blade, the high quality and production efficiency of the film of the low-pressure turbine working blade can be effectively improved, and a foundation is laid for long-life and high-reliability service of the blade.

Description

Technical Field

[0001] The invention relates to the technical field of thin film coating of low-pressure turbine working blades, and in particular to a thin film coating tool for low-pressure turbine working blades. Background Art

[0002] Aircraft engines are known as the "crown jewel of industry" and are the heart of aircraft. The working environment of low-pressure turbine blades is harsh, and they are subjected to the impact and erosion of high-temperature combustion gases for a long time. Their surfaces need to be coated with high-performance films to meet the requirements of high reliability and long service life. At present, there are many technologies for preparing thin films, such as electrochemical deposition based on aqueous solutions and molten salts, chemical vapor deposition, surface diffusion infiltration, and vacuum coating. Compared with other methods, magnetron sputtering technology based on the sputtering physical process has the advantages of low film deposition temperature and precise control of structure and performance. It has been widely used in the preparation of thin films for hot end components of aircraft engines.

[0003] Sputtering refers to the phenomenon that particles with a certain amount of energy bombard the surface of a solid, causing the solid molecules or atoms to leave the solid and be ejected from the surface. Sputtering coating refers to the process of using the sputtering effect produced by particles bombarding the target material to cause the target atoms or molecules to be ejected from the solid surface and deposited on the substrate to form a thin film. Magnetron sputtering is the process of introducing a magnetic field between the two poles of a glow discharge. While the electrons are accelerated by the electric field, they are also bound by the magnetic field, and their motion trajectories form a cycloid, which increases the probability of collision between electrons and charged particles and gas molecules, increases the ionization rate of the gas, and reduces the working gas pressure. + Under the acceleration of the high voltage electric field, the ions collide with the target material and release energy, causing the target atoms on the target surface to escape from the target material and fly to the substrate, where they are deposited to form a thin film. Based on the above analysis, it can be seen that the magnetron sputtering process has a typical line of sight effect, that is, a thin film can be deposited on the surface of the part facing the target material, but high-quality thin film deposition cannot be achieved in the direction away from the target material.

[0004] According to actual needs, the back and basin surfaces of low-pressure turbine working blades need to be coated with thin films, while the tip and tenon areas cannot be coated with thin films. Currently, the main method is to coat the back or basin surface of the blade twice, that is, coating one side of the back or basin surface, and then coating the other side. At this time, it is necessary to break the vacuum, open the furnace door and flip the blade, so there are risks such as interface contamination, and the film coating quality consistency and stability are poor, and the production efficiency is low. Summary of the invention

[0005] In order to solve the problems existing in the prior art, the present invention aims to provide a thin film coating tool which can simultaneously realize thin film deposition on the back and blade basin of a low-pressure turbine working blade, while effectively protecting non-coated areas such as the blade tip and tenon.

[0006] The technical solution adopted by the present invention is: a thin film coating tool for low-pressure turbine working blades, comprising: a support and a planetary gear transmission system located in the support, and a plurality of blade fixture assemblies fixedly connected to the planetary gear transmission system;

[0007] The blade fixture assembly is used to respectively clamp the tenon and the blade crown of the turbine working blade;

[0008] A gear ring is fixedly arranged on the top of the support;

[0009] The planetary gear transmission system drives multiple turbine working blades to revolve around the inside of the gear ring while rotating on their own through the blade clamp assembly;

[0010] The planetary gear transmission system includes a workbench located inside the support, a plurality of supporting legs are provided at the bottom end of the workbench, the top end of the workbench is connected to the positioning seat by bolt connection, the middle part of the positioning seat is rotatably fixedly connected to one end of the main shaft through a through hole, and the other end of the main shaft is fixedly connected to the center of the fixture tray;

[0011] The main shaft is fixedly connected to the sun gear via a flat key;

[0012] A plurality of planetary gears are meshed between the sun gear and the ring gear;

[0013] The fixture tray is provided with a plurality of countersunk holes matching the axis of the planetary gears, and a mandrel with a boss is clamped in each countersunk hole, the bottom end of the mandrel is fixedly connected to the planetary gear, and the top end of the mandrel is fixedly connected to the blade fixture assembly;

[0014] The blade fixture assembly includes a positioning assembly for fixing and protecting the tenon of the turbine working blade and a protective cover assembly for fixing and protecting the blade crown of the turbine working blade;

[0015] Wherein, the positioning assembly comprises a tenon positioning component and a buckle plate, the inner contour of the tenon positioning component matches the curved surface of the tenon edge plate side and the flow channel of the turbine working blade, and a first positioning block is arranged inside the tenon positioning component;

[0016] The end of the buckle plate that matches the tenon positioning component has a shape that matches the edge plate of the turbine working blade and the curved surface at the flow channel, and is provided with a second positioning block;

[0017] Thin pins are provided on the outer sides of the gusset plate and the tenon positioning component, and the two are fixedly connected by binding with steel wire through the thin pins;

[0018] The protective cover assembly is welded by a top plate and side plates, the side plates are completely fitted with the side surfaces of the blade crown and the curved surface of the flow channel, and a through hole is arranged on the top plate.

[0019] The beneficial effect of the present invention is that by adopting the tooling provided by the present invention during the process of thin film coating on the blades, the high quality and production efficiency of the thin film of the low-pressure turbine working blades can be effectively improved, laying the foundation for the long life and high reliability of the blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of a thin film coating tool for low-pressure turbine working blades of the present invention;

[0021] Figure 2 It is a structural schematic diagram of the support of the present invention;

[0022] Figure 3 It is a structural schematic diagram of the planetary gear transmission system of the present invention;

[0023] Figure 4 It is a structural schematic diagram of the limiting plate of the present invention;

[0024] Figure 5 It is a structural schematic diagram of the blade clamp assembly of the present invention;

[0025] Figure 6 It is a structural schematic diagram of the positioning assembly of the present invention;

[0026] Figure 7 It is a schematic diagram of the connection structure between the positioning assembly and the mandrel of the present invention;

[0027] Figure 8 It is a structural schematic diagram of the protective cover assembly of the present invention;

[0028] Among them: 1. Support; 2. Turbine working blades; 3. Blade fixture assembly; 4. Planetary gear transmission system; 5. Planetary gear; 6. Sun gear; 7. Mandrel; 8. Ring gear; 9. Workbench; 10. Support leg; 11. Positioning seat; 12. Spindle; 13. Fixture tray; 14. Flat key; 15. Screw locking retaining ring; 16. Countersunk hole; 17. Bushing; 18. Limit plate; 19. Positioning assembly; 20. Protective cover assembly; 21. Tenon positioning component; 22. Buckle plate; 23. First positioning block; 24. Second positioning block; 25. Thin pin; 26. Mounting seat; 27. Top plate; 28. Side plate. DETAILED DESCRIPTION

[0029] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by those skilled in the art without creative work belong to the scope of protection of the present invention.

[0030] like Figure 1As shown, the present invention provides a low-pressure turbine blade thin film coating tool, comprising: a support 1 and a planetary gear transmission system 4 located in the support 1, and a plurality of blade clamp assemblies 3 fixedly connected to the planetary gear transmission system 4;

[0031] Among them, the support 1 is a hollow cylindrical support, which is used to provide basic support for the entire tooling;

[0032] The blade fixture assembly 3 is used to clamp the turbine working blade 2, and can cover the tenon and blade crown of the turbine working blade 2 when the blade is coated to prevent it from being coated;

[0033] The planetary gear transmission system 4 uses a planetary gear transmission method to drive multiple turbine working blades 2 to revolve around the center of the entire fixture while rotating on their own through the blade fixture assembly 3;

[0034] like Figure 2 As shown, a gear ring 8 is fixedly provided at the top of the support 1 by bolt connection, and the gear ring 8 serves as the orbital track of the planetary gear transmission system 4;

[0035] like Figure 3 As shown, the planetary gear transmission system 4 includes a workbench 9 located inside the support 1, and a plurality of supporting legs 10 are provided at the bottom of the workbench 9 for supporting and adjusting the height thereof, and the top end thereof is connected to a positioning seat 11 by bolt connection, and a cavity is contained between the positioning seat 11 and the workbench 9, which can be used to set a driving device such as a motor;

[0036] The middle part of the positioning seat 11 is rotatably fixedly connected to one end of the main shaft 12 through a through hole, and the other end of the main shaft 12 is fixedly connected to the center of the fixture tray 13;

[0037] The main shaft 12 is fixedly connected to the sun gear 6 via a flat key 14;

[0038] The height of the positioning seat 11 and the workbench 9 needs to match the height of the support 1 to ensure that the sun gear 6 and the ring gear 8 are coaxial;

[0039] A plurality of planetary gears 5 are meshed between the sun gear 6 and the ring gear 8, so that when the sun gear 6 is driven to rotate by the main shaft 12, the planetary gears 5 meshed therewith rotate around their own axes and around the axis of the sun gear 6 on the orbit formed by the ring gear 8;

[0040] Preferably, a screw locking ring 15 may be disposed on the main shaft 12 to prevent the sun gear 6 from axial movement;

[0041] Furthermore, the fixture tray 13 is provided with a plurality of countersunk holes 16 matching the axis of the planetary gear 5, and a mandrel 7 with a boss is clamped in each countersunk hole 16, the bottom end of the mandrel 7 is fixedly connected to the planetary gear 5, and the top end of the mandrel 7 is fixedly connected to the blade fixture assembly 3;

[0042] In this way, when the multiple planetary gears 5 revolve around the sun gear 6 and rotate in the ring gear 8, they can be brought to the blade fixture assembly 3 through the core shaft 7 to achieve the revolution and rotation of the turbine working blades 2;

[0043] Preferably, a bushing 17 is provided between the mandrel 7 and the countersunk hole 16 to facilitate the rotation of the mandrel 7.

[0044] Furthermore, in order to ensure that the ring gear 8 is coaxial with the sun gear 6, a limit plate 18 is provided between the bottom of the support 1 and the support leg 10 of the workbench 9, as shown in FIG. Figure 4 As shown, one end of the limiting plate 18 matches the shape and size of the U-shaped groove at the bottom of the support 1 , and the other end of the limiting plate 18 is provided with a groove for clamping the supporting leg 10 .

[0045] like Figure 5 As shown, the blade fixture assembly 3 includes a positioning assembly 19 for fixing and protecting the tenon of the turbine working blade 2 and a protective cover assembly 20 for fixing and protecting the blade crown of the turbine working blade 2;

[0046] like Figure 6-7 As shown, the positioning assembly 19 is a hollow rectangular box formed by the tenon positioning component 21 and the buckle plate 22. The shape of the internal space of the rectangular box matches the tenon of the turbine working blade 2. Specifically, the internal contour of the tenon positioning component 21 matches the side surface of the tenon edge plate of the turbine working blade 2 and the curved surface at the flow channel, and a first positioning block 23 is provided inside it;

[0047] One end of the buckle plate 22 that cooperates with the tenon positioning component 21 has a shape that matches the edge plate and the curved surface of the flow channel of the turbine working blade 2, and is provided with a second positioning block 24. The outer sides of the buckle plate 22 and the tenon positioning component 21 are both provided with thin pins 25, and the two are fixedly connected by binding with steel wire through the thin pins 25.

[0048] The bottom of the tenon positioning component 21 is used to be fixedly connected to the core shaft 7;

[0049] Furthermore, a test piece mounting seat 26 is welded to the outer side of the gusset plate 22, which can be used to mount a furnace test piece.

[0050] The protective cover assembly 20 is a welded structure. Figure 8As shown, it is welded by a top plate 27 and a side plate 28. The side plate 28 is completely fitted with the side surface of the blade crown and the curved surface at the flow channel. The tip of the blade crown directly touches the top plate 27. The protective cover assembly 20 realizes complete protection of the blade crown. A through hole 29 is provided on the top plate 27, and its position coincides with the position of the groove on the blade. By utilizing the hollow structure of the turbine working blade 2, a steel wire is used from the tenon end of the blade, through the inside of the blade body, and all the way to the blade crown end, and then passed through the hole on the top plate 27 and wrapped around it, thereby realizing a fixed connection of the blade crown.

Claims

1. A thin film coating tool for low-pressure turbine blades, comprising: A support (1), a planetary gear transmission system (4) located in the support (1), and a plurality of blade clamp assemblies (3) fixedly connected to the planetary gear transmission system (4); The blade clamp assembly (3) is used to respectively clamp the tenon and the blade crown of the turbine working blade (2); A gear ring (8) is fixedly disposed on the top end of the support (1); The invention is characterized in that the planetary gear transmission system (4) drives a plurality of turbine working blades (2) through a blade clamp assembly (3) to rotate on their own and revolve around the inside of a gear ring (8) at the same time.

2. The thin film coating tool for low-pressure turbine working blades according to claim 1 is characterized in that: The planetary gear transmission system (4) comprises a workbench (9) located inside the support (1), a plurality of supporting legs (10) are provided at the bottom end of the workbench (9), the top end of the workbench (9) is connected to a positioning seat (11) by bolt connection, the middle part of the positioning seat (11) is rotatably fixedly connected to one end of a main shaft (12) through a through hole, and the other end of the main shaft (12) is fixedly connected to the center of a fixture tray (13); The main shaft (12) is fixedly connected to the sun gear (6) via a flat key (14); A plurality of planetary gears (5) are meshed between the sun gear (6) and the ring gear (8); The fixture tray (13) is provided with a plurality of countersunk holes (16) matching the axis of the planetary gear (5), a core shaft (7) having a boss is clamped in each countersunk hole (16), the bottom end of the core shaft (7) is fixedly connected to the planetary gear (5), and the top end of the core shaft (7) is fixedly connected to the blade fixture assembly (3).

3. The low-pressure turbine blade thin film coating tooling according to claim 2 is characterized in that: The main shaft (12) is provided with a screw locking retaining ring (15).

4. The low-pressure turbine blade thin film coating tooling according to claim 2, characterized in that: A bushing (17) is provided between the core shaft (7) and the countersunk hole (16).

5. The low-pressure turbine blade thin film coating tooling according to claim 2, characterized in that: A limiting plate (18) is arranged between the bottom of the support (1) and the supporting leg (10) of the workbench (9), one end of the limiting plate (18) matches the shape and size of the U-shaped groove at the bottom of the support (1), and the other end of the limiting plate (18) is provided with a groove for clamping the supporting leg (10).

6. The thin film coating tool for low-pressure turbine blades according to claim 1, characterized in that: The blade clamp assembly (3) comprises a positioning assembly (19) for fixing and protecting the tenon of the turbine working blade (2) and a protection cover assembly (20) for fixing and protecting the blade crown of the turbine working blade (2).

7. The thin film coating tool for low-pressure turbine blades according to claim 6, characterized in that: The positioning assembly (19) comprises a tenon positioning component (21) and a buckle plate (22), the inner contour of the tenon positioning component (21) matches the curved surface of the tenon edge plate side and the flow channel of the turbine working blade (2), and a first positioning block (23) is provided inside the tenon positioning component (21); The end of the buckle plate (22) that matches the tenon positioning component (21) has a shape that matches the edge plate and the curved surface of the flow channel of the turbine working blade (2), and is provided with a second positioning block (24); Thin pins (25) are arranged on the outer sides of the buckle plate (22) and the tenon positioning component (21), and the two are fixedly connected by binding with steel wire through the thin pins (25).

8. The thin film coating tool for low-pressure turbine working blades according to claim 7, characterized in that: A test piece mounting seat (26) is welded to the outer side of the gusset plate (22).

9. The thin film coating tool for low-pressure turbine blades according to claim 6, characterized in that: The protective cover assembly (20) is formed by welding a top plate (27) and a side plate (28); the side plate (28) is completely fitted with the side surface of the blade crown and the curved surface of the flow channel; and a through hole (29) is provided on the top plate (27).

Images