A fully automatic spraying device for aviation and aerospace turbine blades

Abstract

The present invention relates to the field of thermal spray coating technology, specifically to a fully automatic spraying device for aviation and aerospace turbine blades. The device includes a spraying manipulator and a spraying workbench. The plasma spray gun is linked to the spraying workbench through the spraying manipulator. The tailstock positioning, telescopic and locking mechanism and the power transmission system are relatively arranged on the base of the spraying workbench. The turbine blade is installed between the clamping tooling composed of the tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism and the axial air-cooled rotating main shaft of the power transmission system; the turbine blade is clamped by the axial air-cooled rotating main shaft of the power transmission system and the tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism, and driven by the indexing positioner of the power transmission system to achieve 360° indexing positioning. The present invention utilizes the spraying manipulator and the spraying workbench to achieve indexing positioning and flexible cooperation, so as to realize the spraying of the profiles and edge plate positions of the blades of aviation and aerospace turbine blades with different curvatures.

Description

Technical Field

[0001] The invention relates to the technical field of thermal spray coatings, in particular to a fully automatic spraying device for aviation and aerospace turbine blades. Background Art

[0002] The thermal barrier coating prepared by the electron beam physical vapor deposition (EB-PVD) process for advanced aero-engine turbine blades has insufficient thermal insulation performance and premature peeling during the test run, which has become a long-standing technical problem in the engine development process. Domestic aviation factories and design institutes have carried out a lot of research work on the performance research and preparation process optimization of thermal barrier coatings for turbine guide blades, and have made breakthrough progress. At present, it is determined that the use of atmospheric plasma spraying technology (APS) to replace EB-PVD is the key means to solve this problem. Since the turbine blades of aviation and aerospace engines are double-linked structures and have complex surfaces, there are local obstructions between adjacent blades, and the curvature of the blade and edge plate spraying surface is large, which brings great difficulties to automated spraying. In addition, since the turbine blades use single crystals as the substrate material, the blade substrate temperature must be controlled during the spraying process. All of the above are major challenges in the plasma spraying process. Perfectly coupling the high-precision intelligent linkage workbench with the spray gun and cooling system to solve the problems of obstruction and substrate overheating during the spraying process is an important technology for realizing automated spraying of turbine blades. To ensure uniform coating thickness and performance stability, angle control during spraying is particularly important, which places higher technical requirements on the spraying workbench. Summary of the invention

[0003] In order to solve the above problems and realize the preparation of thermal barrier coatings on the outer surfaces of turbine blades of hot end components of aviation and aerospace engines with complex surfaces, the purpose of the present invention is to provide a fully automatic spraying device for aviation and aerospace turbine blades, which can enable the plasma spray gun to spray at high stability and multiple angles when executing complex paths, thereby realizing the preparation of thermal barrier coatings on the outer surfaces of turbine blades of hot end components of aviation and aerospace with complex surfaces, and can effectively and stably control the performance and quality of thermal barrier coatings on the outer surfaces of turbine blades of hot end components with complex surfaces, thereby improving production efficiency.

[0004] In order to achieve the above-mentioned purpose, the technical solution of the present invention is: A fully automatic spraying device for aviation and aerospace turbine blades, the device comprises a spraying manipulator and a spraying workbench, the spraying manipulator is mounted on a manipulator base, a plasma spray gun is mounted on the spraying manipulator, and the plasma spray gun is linked with the spraying workbench through the spraying manipulator; a tailstock positioning, telescopic and locking mechanism and a power transmission system are relatively arranged on the base of the spraying workbench, and the turbine blade is mounted between a clamping fixture composed of a tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism and an axial air-cooled rotary main shaft of the power transmission system; the turbine blade is clamped by the axial air-cooled rotary main shaft of the power transmission system and the tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism, and driven by a dividing positioner of the power transmission system to achieve 360° indexing positioning.

[0005] The fully automatic spraying device for aviation and aerospace turbine blades has a power transmission system including an external shaft servo motor, a synchronous belt transmission device, a dividing positioner, and an axial air-cooled rotary spindle. The output end of the external shaft servo motor is connected to one end of the horizontal axial air-cooled rotary spindle through a synchronous belt transmission device, and a dividing positioner is installed on the axial air-cooled rotary spindle. The power transmission system is linked to the spraying robot through the external shaft servo motor, and the external shaft servo motor drives the synchronous belt transmission device through a planetary reducer.

[0006] The fully automatic spraying device for aviation and aerospace turbine blades, the tailstock positioning, telescopic and locking mechanism includes a tailstock telescopic device, a locking device, a pneumatic booster, a tailstock support base, and a displacement screw. The upper part of the tailstock support base is provided with a tailstock telescopic device and a locking device, one end of the horizontal tailstock telescopic device is connected to the locking device, the other end of the tailstock telescopic device corresponds to the other end of the axial air-cooled rotary spindle and clamps the turbine blades, a pneumatic booster is installed on the side of the tailstock support base, and the lower part of the tailstock support base is drivingly connected to the horizontal displacement screw on the base.

[0007] The fully automatic spraying device for aviation and aerospace turbine blades has a tailstock telescopic device that fixes the turbine blades by telescoping the cylinder, and a tailstock support base that accurately positions the tailstock support base by a displacement screw, with a positioning accuracy of ±0.1mm.

[0008] The fully automatic spraying device for aviation and aerospace turbine blades is also provided with an input cooling air control system and a spray cooling device on the base. A cooling air inlet is provided at one end of the input cooling air control system. The cooling air inlet is connected to one end of the hollow inner cavity of the axial air-cooled rotating main shaft. The other end of the hollow inner cavity of the axial air-cooled rotating main shaft is connected to the inner cavity of the turbine blade. The top of the spray cooling device corresponds to the outside of the turbine blade.

[0009] The fully automatic spraying device for aviation and aerospace turbine blades has a cooling air input port and a cooling air output port at both ends of the inner cavity of the turbine blade, the cooling air input port is connected to the axial air-cooled rotary spindle, and the cooling air output port is connected to the tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism.

[0010] The fully automatic spraying device for aviation and aerospace turbine blades has a powder collecting device disposed above the base, and the powder collecting device is located on a side of the turbine blade corresponding to the spraying direction.

[0011] The fully automatic spraying device for aviation and aerospace turbine blades is also provided with a control system on the base, and the control system is linked with the spraying manipulator through the program output signal set by the programmable controller PLC.

[0012] The fully automatic spraying device for aviation and aerospace turbine blades has an ABB six-axis spraying robot.

[0013] The design idea of ​​the present invention is: The present invention adopts a modular design concept, designs independent support structures and accessories for the unique connection structure and size of aviation and aerospace turbine blades, adopts a tailstock positioning, telescopic and locking mechanism to fix and lock the turbine blades, and cooperates with the spraying robot through the external shaft servo motor. Each component is flexible and adjustable and easy to replace, and the program of each part can be set according to different spraying angle requirements to achieve spraying of complex surfaces of turbine blades and expand the scope of use of the device. The present invention can perfectly couple the high-precision intelligent linkage workbench with the plasma spray gun and cooling system through the effective coordination of a series of accessories such as the spraying robot linkage power transmission system, the tailstock positioning, telescopic and locking mechanism, the input cooling air control system, the powder collection device, the spray cooling device, and the control system, thereby solving the problems of shielding and substrate overheating during the spraying process. It is an important technology for realizing the automated spraying of turbine blades. In order to ensure the uniformity of coating thickness and performance stability, angle control during spraying is particularly important. Therefore, higher technical requirements are also put forward for spraying equipment. By using the coordinated linkage between the spraying robot and the spraying workbench, a flexible spraying technology has been developed to realize the automated spraying of complex surfaces of aviation and aerospace engine turbine blades, breaking through the problems of low coating bonding strength and poor thickness uniformity, and meeting the use requirements of aviation and aerospace engines.

[0014] The advantages and beneficial effects of the present invention are: 1. The fully automatic spraying device of the present invention comprises a spraying robot and a spraying workbench linked with the spraying robot. The spraying workbench consists of a base, a control system, an input cooling air control system, a powder collecting device, a spraying cooling device, a tailstock positioning telescopic and locking mechanism, a power transmission system, etc., which can make the plasma spray gun highly stable and spray at multiple angles when executing complex paths, realize the preparation of thermal barrier coatings on the outer surfaces of turbine blades of hot end components with complex surfaces in aviation and aerospace, and can effectively and stably control the performance and quality of thermal barrier coatings on the outer surfaces of turbine blades of hot end components with complex surfaces, thereby improving production efficiency.

[0015] 2. The present invention utilizes a spraying robot and a spraying workbench to realize indexing positioning and flexible coordination, so as to realize spraying of the profiles and edge plates of aviation and aerospace turbine blades with different curvatures, and integrates the irregular surfaces of single-blade and double-blade turbine blades and edge plates, and is used for the preparation of thermal barrier coatings for the surfaces of aviation and aerospace turbine hot end components with irregular surfaces on the entire surface of the parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The present invention is a schematic diagram of the installation structure of the fully automatic spraying device for aviation and aerospace turbine blades.

[0017] Figure 2 This is the assembly front view of the spraying workbench.

[0018] Figure 3 This is a schematic diagram of the blade clamping device structure.

[0019] In the figure, 11 spraying robot, 12 base, 13 control system, 14 input cooling air control system, 15 powder collecting device, 16 turbine blades, 17 robot base, 18 spray cooling device, 19 tailstock positioning, telescopic and locking mechanism; 21 external axis servo motor, 22 synchronous belt transmission device, 23 indexing positioner, 24 tailstock telescopic device, 25 locking device, 26 pneumatic booster, 27 displacement screw; 31 cooling air inlet, 32 axial air-cooled rotary spindle, 33 power transmission system, 34 tailstock support base. DETAILED DESCRIPTION

[0020] The fully automatic spraying device for aviation and aerospace turbine blades of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0021] See also Figure 1 , Figure 2 , Figure 3The present invention preferably implements the application of the fully automatic spraying device for aviation and aerospace turbine blades. The installation structure of the fully automatic spraying device for aviation and aerospace turbine blades mainly includes a spraying manipulator 11 and a spraying workbench. The spraying manipulator 11 is installed on the manipulator base 17. A plasma spray gun is installed on the spraying manipulator 11. The plasma spray gun is linked with the spraying workbench through the spraying manipulator to perform fully automatic spraying on the blade body and edge plate of aviation and aerospace turbine blades. The spraying workbench includes a base 12, a control system 13, an input cooling air control system 14, a powder collection device 15, a spray cooling device 18, a tailstock positioning telescopic and locking mechanism 19 (tailstock telescopic device 24, locking device 25, pneumatic booster 26, tailstock support base 34, displacement screw 27), a power transmission system 33 (external shaft servo motor 21, synchronous belt transmission device 22, indexing positioner 23, axis air-cooled rotary spindle 32), and the specific structure is as follows: The tailstock positioning, telescopic and locking mechanism 19 and the power transmission system 33 are relatively arranged on the base 12, and the turbine blade 16 is installed between the clamping tooling composed of the tailstock telescopic device 24 of the tailstock positioning, telescopic and locking mechanism 19 and the axial air-cooled rotating main shaft 32 of the power transmission system 33; the turbine blade 16 is clamped by the axial air-cooled rotating main shaft 32 of the power transmission system 33 and the tailstock telescopic device 24 of the tailstock positioning, telescopic and locking mechanism 19, and driven by the indexing locator 23 of the power transmission system 33 to achieve 360° high-precision indexing positioning.

[0022] The power transmission system 33 includes an external shaft servo motor 21, a synchronous belt transmission device 22, a dividing positioner 23, and an axial air-cooled rotary spindle 32. The output end of the external shaft servo motor 21 is connected to one end of the horizontal axial air-cooled rotary spindle 32 through the synchronous belt transmission device 22. The dividing positioner 23 is installed on the axial air-cooled rotary spindle 32. The power transmission system 33 is linked to the spraying robot 11 through the external shaft servo motor 21, and the external shaft servo motor 21 drives the synchronous belt transmission device 22 through a precision planetary reducer.

[0023] The tailstock positioning, telescopic and locking mechanism 19 includes a tailstock telescopic device 24, a locking device 25, a pneumatic booster 26, a tailstock support base 34, and a displacement screw 27. The tailstock telescopic device 24 and the locking device 25 are provided on the upper part of the tailstock support base 34. One end of the horizontal tailstock telescopic device 24 is connected to the locking device 25. The other end of the tailstock telescopic device 24 corresponds to the other end of the axial air-cooled rotary spindle 32 and clamps the turbine blade 16. The pneumatic booster 26 is installed on the side of the tailstock support base 34. The lower part of the tailstock support base 34 is connected to the horizontal displacement screw 27 on the base 12. The tailstock telescopic device 24 fixes the turbine blade 16 through the cylinder telescopic, and has a locking function to ensure the stability of the turbine blade 16 during the spraying process. The tailstock support base 34 moves horizontally through the displacement screw 27 (ball screw), which guarantees the running trajectory and stability. The displacement screw 27 can accurately position the tailstock support base 34, and the positioning accuracy can reach ±0.1mm. The tailstock telescopic device 24 and the locking device 25 are responsible for buffering the hard contact between the turbine blades 16 and the tailstock support base 34 to reduce the collision of the turbine blades 16. The locking device 25 prevents the influence of pressure relief on the clamping of the turbine blades 16 during power failure.

[0024] The base 12 is also provided with an input cooling air control system 14 and a spray cooling device 18. A cooling air inlet 31 is provided at one end of the input cooling air control system 14. The cooling air inlet 31 is connected to one end of the hollow inner cavity of the axial air-cooled rotating main shaft 32. The other end of the hollow inner cavity of the axial air-cooled rotating main shaft 32 is connected to the inner cavity of the turbine blade 16. The upper side of the spray cooling device 18 corresponds to the outside of the turbine blade 16. The spray cooling device 18 mainly protects the blade clamping tooling and the cooling of the blade spraying process. A cooling gas input port and a cooling gas output port are respectively provided at both ends of the inner cavity of the turbine blade 16. The cooling gas input port is connected to the axial air-cooled rotating spindle 32, and the cooling gas output port is connected to the tailstock telescopic device 24 of the tailstock positioning, telescopic and locking mechanism 19. The cooling gas output port provides internal cooling for the spraying process of the turbine blade 16. At the same time, the gas coming out of the cooling gas output port is used to blow the surface of the cylinder sealing surface of the tailstock telescopic device 24 to prevent the dust generated during the spraying process from affecting the telescopic mechanism, thereby effectively ensuring the stable telescopicity of the cylinder.

[0025] The powder collecting device 15 is arranged above the base 12 and is located on the side of the turbine blade 16 corresponding to the spraying direction. The powder collecting device 15 recovers and protects the dust generated by the entire device during the spraying process, effectively ensuring the normal operation and work of the device.

[0026] A control system 13 is also provided on the base 12 , and the control system 13 is connected to the spraying robot 11 , the external shaft servo motor 21 , and the pneumatic booster 26 through a programmable controller PLC, so as to perform linkage control on the spraying robot 11 , the external shaft servo motor 21 , and the pneumatic booster 26 .

[0027] The control system 13 is equipped with control elements such as a programmable controller PLC, a servo motor driver, a flow sensor, and a pressure sensor. The program output signal is set by the programmable controller PLC to link with the spraying robot 11, and the gas flow input to the cooling gas control system 14 is regulated, and the blades are sprayed in combination with the tailstock telescopic device 24. The programmable controller uses Panasonic FP-XH general-purpose PLC, and the equipment control is realized through software programming; the programmable controller PLC is responsible for collecting equipment status signals, operation signals such as buttons, and feedback signals such as limit switches and sensors; the programmable controller PLC accurately controls the speed and position of the external axis servo motor through the bus or pulse output module to ensure the system response speed.

[0028] The spraying workbench and the spraying manipulator 11 are linked and coordinated. According to the structural characteristics of the blade, a flexible spraying technology is developed. The spraying process is controlled by the control system 13 to control the spraying speed, spraying angle, etc. The input cooling gas control system 14 controls the internal gas flow of the blade and the external spray cooling device 18 of the blade to cool the blade in real time. The excess dust generated during the spraying process is recycled and processed by the powder collection device 15. Through the above linkage, the walking path of the spraying program can be effectively and stably controlled, and the spraying of different angles of complex surfaces is solved, and the spraying efficiency and coating performance quality stability are improved. The present invention realizes the linkage between the spraying workbench and the spraying manipulator 11, and the turbine blade 16 is fixed by the clamping tool composed of the axial air-cooled rotary spindle 32 and the tailstock telescopic device 24. The turbine blade 16 is driven by the synchronous belt transmission device 22 on the external shaft servo motor 21 to achieve indexing positioning, solving the problem of spraying different curved surfaces of the blade. During the spraying process, the blade is sprayed and cooled in cooperation with the spraying manipulator 11 according to the set parameters, which can effectively ensure the uniformity of the temperature of the spray substrate of the turbine blade 16 and the coating thickness.

[0029] In this embodiment, the synchronous belt transmission device 22 is driven by the external shaft servo motor 21, and the turbine blades 16 are clamped by the axial air-cooled rotating main shaft 32 and the tailstock positioning, telescopic and locking mechanism 19 to perform 360° spraying without dead angles. The external shaft servo motor 21 and the spraying robot 11 can be controlled in linkage, and the plasma spray gun is cooperated to achieve spraying according to the required rotation speed and angle. After the spraying is completed, the telescopic driving force of the tailstock can be adjusted by the pressure reducing valve. After the tailstock is extended, the spring locking position is released, the air pressure is reduced and the tailstock is retracted, and the turbine blades 16 are removed to complete the spraying.

[0030] In this embodiment, the spraying robot 11 and the external shaft servo motor 21 can be flexibly coordinated to realize the rotation of the turbine blades along with the movement of the plasma spray gun during the program design process. Combined with the unique structural characteristics of the turbine blades 16, the high-precision intelligent linkage workbench is perfectly coupled with the spray gun and the cooling system to solve the problems of obstruction and overheating of the substrate during the spraying process. This is an important technology for realizing the automated spraying of turbine blades and ensuring the uniformity of coating thickness and performance stability.

[0031] In this embodiment, the external axis servo motor 21 can adopt ABB MU series external axis servo motor (such as ABB MUGU-516937 external axis servo motor), and the spraying robot 11 can adopt ABB six-axis robot produced by ABB (Asea Brown Boveri).

[0032] The results of the embodiments show that the present invention provides a fully automatic spraying device for aviation and aerospace turbine blades, which realizes the preparation of thermal barrier coatings on the outer surfaces of hot end component turbine blades with complex surfaces of aviation and aerospace engines, and enables the plasma spray gun to spray with high stability and multiple angles when executing complex paths, thereby realizing the preparation of thermal barrier coatings on the outer surfaces of hot end component turbine blades with complex surfaces of aviation and aerospace engines, and can effectively and stably control the performance and quality of thermal barrier coatings for the outer surfaces of hot end component turbine blades with complex surfaces, thereby improving production efficiency. Thus, the requirements for the preparation of thermal barrier coatings on the outer surfaces of hot end component turbine blades with complex surfaces of aviation and aerospace engines are met.

Claims

1. A fully automatic spraying device for aviation and aerospace turbine blades, characterized in that: The device comprises a spraying manipulator and a spraying workbench. The spraying manipulator is mounted on a manipulator base, a plasma spray gun is mounted on the spraying manipulator, and the plasma spray gun is linked to the spraying workbench through the spraying manipulator; a tailstock positioning, telescopic and locking mechanism and a power transmission system are relatively arranged on the base of the spraying workbench, and a turbine blade is mounted between a clamping fixture composed of a tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism and an axial air-cooled rotary spindle of the power transmission system; the turbine blade is clamped by the axial air-cooled rotary spindle of the power transmission system and the tailstock telescopic device of the tailstock positioning, telescopic and locking mechanism, and driven by a dividing positioner of the power transmission system to achieve 360° indexing positioning.

2. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1, characterized in that: The power transmission system includes an external shaft servo motor, a synchronous belt transmission device, a dividing positioner, and an axial air-cooled rotary spindle. The output end of the external shaft servo motor is connected to one end of the horizontal axial air-cooled rotary spindle through the synchronous belt transmission device. The dividing positioner is installed on the axial air-cooled rotary spindle. The power transmission system is linked to the spraying robot through the external shaft servo motor, and the external shaft servo motor drives the synchronous belt transmission device through a planetary reducer.

3. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1 is characterized in that: The tailstock positioning, telescopic and locking mechanism comprises a tailstock telescopic device, a locking device, a pneumatic booster, a tailstock support base and a displacement screw. The upper part of the tailstock support base is provided with a tailstock telescopic device and a locking device. One end of the horizontal tailstock telescopic device is connected with the locking device, and the other end of the tailstock telescopic device corresponds to the other end of the axial air-cooled rotary spindle and clamps the turbine blades. A pneumatic booster is installed on the side of the tailstock support base, and the lower part of the tailstock support base is drivingly connected with the horizontal displacement screw on the base.

4. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 3 is characterized in that: The tailstock telescopic device fixes the turbine blades through cylinder telescopic movement, and the tailstock support base is precisely positioned by the displacement screw, with a positioning accuracy of ±0.1mm.

5. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1 is characterized in that: The base is also provided with an input cooling air control system and a spray cooling device. A cooling air inlet is provided at one end of the input cooling air control system. The cooling air inlet is connected to one end of the hollow inner cavity of the axial air-cooled rotating spindle. The other end of the hollow inner cavity of the axial air-cooled rotating spindle is connected to the inner cavity of the turbine blade. The top of the spray cooling device corresponds to the outside of the turbine blade.

6. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 5, characterized in that: A cooling air input port and a cooling air output port are respectively provided at both ends of the inner cavity of the turbine blade. The cooling air input port is connected to the axial air-cooled rotary spindle, and the cooling air output port is connected to the tailstock telescopic device of the tailstock positioning telescopic and locking mechanism.

7. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1, characterized in that: A powder collecting device is arranged above the base, and the powder collecting device is located on one side of the turbine blade corresponding to the spraying direction.

8. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1 is characterized in that: A control system is also provided on the base, and the control system is linked with the spraying robot through a program output signal set by a programmable controller PLC.

9. The fully automatic spraying device for aviation and aerospace turbine blades according to claim 1, characterized in that: The spraying robot is an ABB six-axis robot.

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