An annular fixture for laser peening of turbine blades of an aeroengine

Abstract

The application provides a kind of aviation engine turbine blade laser shot peening ring clamp, it is related to turbine blade processing technical field.The aviation engine turbine blade laser shot peening ring clamp, including annular mounting table, the inner wall of the annular mounting table is fixedly connected with cross fixed seat, the upper surface middle part of the cross fixed seat is connected with positioning placement assembly, the upper surface of the annular mounting table is rotatably connected with threaded rotating rod.The application, start third drive cylinder, the piston end of third drive cylinder moves with the connection fixed disc, so that fourth servo motor is close to the curved blade with two blade clamping plates through rectangular mounting plate, so that two blade clamping plates are located at the two sides of curved blade, by starting fourth servo motor, the output shaft of fourth servo motor rotates with rectangular mounting plate, rectangular mounting plate rotates with two blade clamping plates, the angle of two blade clamping plates can be changed, suitable for different turbine blades, and the adaptation degree is high.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of turbine blade processing technology, in particular to a ring-shaped clamp for laser shot peening of an aero-engine turbine blade. BACKGROUND

[0002] Laser shot peening is a surface treatment method that effectively improves the service life of parts by forming a compressive stress layer on the surface of the parts through high-energy shock waves induced by strong pulsed laser. This treatment method is commonly used in high-precision parts such as aero-engine blades and automotive precision gears. With the progress of society, China's industrial level has grown rapidly, and automated laser shot peening has become a popular development in shot peening technology.

[0003] The clamp is one of the important components of the laser shot peening equipment. Most of the current laser shot peening clamps are mechanical clamps. Due to the irregularity of the curved surface of the engine turbine blade, the traditional clamp is difficult to adapt to different curved turbine blades during clamping, and may cause clamping instability or even damage to the blade. At the same time, the clamped part cannot be treated by laser shot peening after clamping, and cannot be turned over, often requiring removal and re-clamping, resulting in low processing efficiency. SUMMARY

[0004] (I) Technical problems solved

[0005] To solve the problems of the prior art, the present application provides a ring-shaped clamp for laser shot peening of an aero-engine turbine blade, which solves the problems of the traditional clamp being difficult to adapt to different curved turbine blades and low processing efficiency.

[0006] (II) Technical solutions

[0007] In order to achieve the above object, the present application is realized by the following technical scheme: An annular clamp for laser shot peening of turbine blades of an aero-engine, comprising an annular mounting table, a cross fixed seat is fixedly connected to the inner wall of the annular mounting table, a positioning and placing assembly is connected to the middle of the upper surface of the cross fixed seat, a threaded rotating rod is rotatably connected to the upper surface of the annular mounting table, a first lifting sleeve block is threadedly connected to the outer surface of the threaded rotating rod, a first power assembly for driving the threaded rotating rod to rotate is mounted on the upper surface of the cross fixed seat, three vertical guide posts are fixedly connected to the upper surface of the annular mounting table, a second lifting sleeve block is sleeved on the outer surface of one of the vertical guide posts, a third lifting sleeve block is sleeved on the outer surface of the other two vertical guide posts, a lifting linkage ring is fixedly connected to the outer sides of the first lifting sleeve block, the second lifting sleeve block and the third lifting sleeve block, a rotating mounting shaft is rotatably connected to each of the opposite sides of the first lifting sleeve block and the second lifting sleeve block, a turnover mounting ring is arranged in the middle of the two rotating mounting shafts, four mounting protrusions arranged in an annular array are fixedly connected to the outer surface of the turnover mounting ring, the opposite ends of the two rotating mounting shafts are fixedly connected to the corresponding mounting protrusions, a second power assembly for driving the rotating mounting shaft to rotate is mounted on the inner wall of the lifting linkage ring, a limiting assembly is mounted on each of the opposite sides of the two third lifting sleeve blocks, a rotating mounting ring is rotatably connected to the upper surface of the turnover mounting ring, a third power assembly for driving the rotating mounting ring to rotate is mounted on the outer side wall of the turnover mounting ring, four arc-shaped mounting grooves arranged in an annular array are formed in the upper surface of the rotating mounting ring, a moving mounting block is slidably connected in the arc-shaped mounting groove, a fourth power assembly for driving the moving mounting block to move is mounted on the upper surface of the rotating mounting ring, and a clamping assembly is mounted in the moving mounting block.

[0008] Preferably, the positioning and placing assembly comprises a vertical fixed column fixedly connected to the upper surface of the cross fixed seat, a through positioning column is fixedly connected to the top of the vertical fixed column, and a limiting mounting disc is fixedly connected to the outer surface of the through positioning column.

[0009] Preferably, the first power assembly comprises a first servo motor fixedly connected to the upper surface of the cross fixed seat, a first pulley is fixedly connected to the output shaft of the first servo motor, a second pulley is fixedly connected to the outer surface of the threaded rotating rod, the first pulley and the second pulley are drivingly connected through a first belt, the first servo motor is started, the output shaft of the first servo motor rotates with the first pulley, the threaded rotating rod rotates, the first lifting sleeve block, the second lifting sleeve block and the third lifting sleeve block descend with the turnover mounting ring, and the turnover mounting ring descends with the rotating mounting ring.

[0010] Preferably, the second power assembly comprises a third servo motor fixedly connected to the inner wall of the lifting linkage ring, the output shaft of the third servo motor is fixedly connected with a third belt pulley, the outer surface of the rotating installation shaft is fixedly connected with a fourth belt pulley, the third belt pulley and the fourth belt pulley are drivingly connected through a second belt, the third servo motor is started, the output shaft of the third servo motor rotates with the third belt pulley, the rotating installation shaft rotates with the overturning installation ring, and the rotating installation ring rotates with the engine turbine blade.

[0011] Preferably, the limiting assembly comprises a first drive cylinder fixedly connected to the outer wall of the third lifting sleeve block, the piston end of the first drive cylinder is fixedly connected with a limiting protruding rod, one end of the limiting protruding rod away from the first drive cylinder is clamped with a corresponding installation protruding block, and a clamping hole matched with the installation protruding block is formed in the side wall of the installation protruding block.

[0012] Preferably, the third power assembly comprises an installation fixing seat fixedly connected to the outer side wall of the overturning installation ring, the upper surface of the installation fixing seat is fixedly connected with a second servo motor, the output shaft of the second servo motor is fixedly connected with a rotating gear, the outer side wall of the rotating installation ring is fixedly connected with a rotating outer gear ring, the rotating gear is meshingly connected with the rotating outer gear ring, the second servo motor is started, the output shaft of the second servo motor rotates with the rotating gear, the rotating gear rotates with the rotating outer gear ring, the rotating outer gear ring rotates with the rotating installation ring, and the rotating installation ring rotates with the engine turbine blade to perform rotating shot blasting.

[0013] Preferably, the fourth power assembly comprises a second drive cylinder rotationally connected to the upper surface of the rotating installation ring, the piston end of the second drive cylinder is fixedly connected with a connecting shaft, one end of the connecting shaft away from the second drive cylinder is rotationally connected with a connecting rectangular block, and the connecting rectangular block is fixedly connected to the side wall of the moving installation block, the second drive cylinder is started, the piston end of the second drive cylinder moves with the connecting rectangular block through the connecting shaft, the connecting rectangular block moves with the moving installation block in the arc-shaped installation groove, and the blade clamping plate is moved to the curved blade that has been shot blasted.

[0014] Preferably, the clamping assembly comprises a third drive cylinder fixedly connected to the inside of the movable mounting block, the piston end of the third drive cylinder is fixedly connected with a connecting fixed disc, the side wall of the connecting fixed disc is fixedly connected with a fourth servo motor, the output shaft of the fourth servo motor is fixedly connected with a rectangular mounting plate, the side wall of the rectangular mounting plate is slidably connected with two inclined blade clamping plates, the opposite side of the two blade clamping plates is fixedly connected with a fixed soft pad plate, the side wall of the rectangular mounting plate is fixedly connected with two mounting rectangular blocks, the side wall of the mounting rectangular block is fixedly connected with a fourth drive cylinder, the piston end of the fourth drive cylinder is fixedly connected with the corresponding blade clamping plate, the third drive cylinder is started, the piston end of the third drive cylinder moves with the connecting fixed disc, so that the fourth servo motor moves with the two blade clamping plates through the rectangular mounting plate to the curved blade, so that the two blade clamping plates are located on both sides of the curved blade, the fourth servo motor is started, the output shaft of the fourth servo motor rotates with the rectangular mounting plate, and the rectangular mounting plate rotates with the two blade clamping plates.

[0015] Preferably, the lower surface of the movable mounting block is fixedly connected with a sliding block, and the sliding block is slidably connected in the arc-shaped mounting groove.

[0016] (Three) beneficial effects

[0017] The application provides an annular clamp for laser peening of turbine blades of an aero-engine.

[0018] 1、the application, the third drive cylinder is started, the piston end of the third drive cylinder moves with the connecting fixed disc, so that the fourth servo motor moves with the two blade clamping plates through the rectangular mounting plate to the curved blade, so that the two blade clamping plates are located on both sides of the curved blade, the fourth servo motor is started, the output shaft of the fourth servo motor rotates with the rectangular mounting plate, and the rectangular mounting plate rotates with the two blade clamping plates, the angle of the two blade clamping plates can be changed, which is suitable for different turbine blades and has high adaptability.

[0019] 2、the application, first loosen the curved blade of the two groups of oppositely arranged blade clamping plates, the third drive cylinder moves with the blade clamping plate to reset, then the second drive cylinder is started, the piston end of the second drive cylinder moves with the connecting rectangular block through the connecting shaft, the connecting rectangular block moves with the movable mounting block in the arc-shaped mounting groove, the blade clamping plate is moved to the curved blade that has been treated by laser peening, and clamping is performed again through the blade clamping plate, the other two groups of blade clamping plates are moved in the above manner, laser peening treatment is performed on the curved blade that has not been treated by the equipment, and the treatment is more comprehensive.

[0020] 3、The first drive cylinder of the application, the piston end of the first drive cylinder with the limit convex rod retracts, so that the limit convex rod is separated from the mounting block, then the third servo motor is started, the output shaft of the third servo motor rotates with the third belt pulley, so that the rotating mounting shaft rotates with the turnover mounting ring, the rotating mounting ring rotates with the engine turbine blade, after the turnover is completed, the first drive cylinder is started, so that the limit convex rod is connected with the mounting block, according to the above-mentioned mode, the other side of the engine turbine blade is processed by laser shot peening, and the processing efficiency is high.

[0021] 4、The second servo motor of the application is started, the output shaft of the second servo motor rotates with the rotating gear, the rotating gear rotates with the rotating outer gear ring, the rotating outer gear ring rotates with the rotating mounting ring, and the rotating mounting ring rotates with the engine turbine blade to rotate and spray. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 A perspective structural schematic view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application;

[0023] Figure 2 A top view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application;

[0024] Figure 3 A rotating mounting ring structure schematic view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application;

[0025] Figure 4 A rotating mounting ring structure schematic view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application; Figure 3 An enlarged schematic view of the middle A;

[0026] Figure 5 A moving mounting block structure schematic view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application;

[0027] Figure 6 A blade clamping plate structure schematic view of the annular clamp for laser shot peening of the turbine blade of the aero-engine is provided for the application.

[0028] The components include: 1. Annular mounting platform; 2. Cross-shaped fixing seat; 3. Vertical fixing column; 4. Through-positioning column; 5. Limiting mounting disc; 6. Threaded rotating rod; 7. First lifting sleeve block; 8. First servo motor; 9. Vertical guide rod; 10. Second lifting sleeve block; 11. Third lifting sleeve block; 12. Lifting linkage ring; 13. Rotary mounting shaft; 14. Flipping mounting ring; 15. Mounting protrusion; 16. First drive cylinder; 17. Limiting protrusion; 18. Rotary mounting... 19. Rotating external gear ring; 20. Mounting base; 21. Second servo motor; 22. Rotating gear; 23. Third servo motor; 24. Moving mounting block; 25. Second drive cylinder; 26. Connecting rectangular block; 27. Third drive cylinder; 28. Connecting mounting plate; 29. ​​Fourth servo motor; 30. Rectangular mounting plate; 31. Blade clamping plate; 32. Fixing soft pad plate; 33. Mounting rectangular block; 34. Fourth drive cylinder; 35. Arc-shaped mounting groove. Detailed Implementation

[0029] The technical solutions of the embodiments 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, and 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.

[0030] Example:

[0031] like Figures 1-6 As shown, this embodiment of the invention provides an annular fixture for laser shot peening of aero-engine turbine blades, including an annular mounting platform 1. A cross-shaped fixing seat 2 is fixedly connected to the inner wall of the annular mounting platform 1. A positioning and placement assembly is connected to the middle of the upper surface of the cross-shaped fixing seat 2. The positioning and placement assembly includes a vertical fixing post 3 fixedly connected to the upper surface of the cross-shaped fixing seat 2. A through-positioning post 4 is fixedly connected to the top of the vertical fixing post 3. A limiting mounting disk 5 is fixedly connected to the outer surface of the through-positioning post 4. The center hole of the engine turbine blade is inserted into the through-positioning post 4, and the engine turbine blade is placed on the limiting mounting disk 5.

[0032] The upper surface of the annular mounting table 1 is rotationally connected with a threaded rotating rod 6, the outer surface of the threaded rotating rod 6 is threadedly connected with a first lifting sleeve block 7, the upper surface of the cross fixed seat 2 is provided with a first power assembly for driving the threaded rotating rod 6 to rotate, the first power assembly comprises a first servo motor 8 fixedly connected to the upper surface of the cross fixed seat 2, the output shaft of the first servo motor 8 is fixedly connected with a first belt pulley, the outer surface of the threaded rotating rod 6 is fixedly connected with a second belt pulley, the first belt pulley and the second belt pulley are drivingly connected through a first belt, the first servo motor 8 is started, the output shaft of the first servo motor 8 drives the first belt pulley to rotate, so that the threaded rotating rod 6 rotates, so that the first lifting sleeve block 7, the second lifting sleeve block 10 and the third lifting sleeve block 11 drive the turnover mounting ring 14 to descend, and the turnover mounting ring 14 drives the rotating mounting ring 18 to descend;

[0033] The upper surface of the annular mounting table 1 is fixedly connected with three vertical guide vertical rods 9, the outer surface of one of the vertical guide vertical rods 9 is sleeved with a second lifting sleeve block 10, and the outer surfaces of the other two vertical guide vertical rods 9 are both sleeved with a third lifting sleeve block 11, the outer sides of the first lifting sleeve block 7, the second lifting sleeve block 10 and the third lifting sleeve block 11 are fixedly connected with a lifting linkage ring 12, the first lifting sleeve block 7, the second lifting sleeve block 10 and the third lifting sleeve block 11 can be synchronously lifted and descended through the lifting linkage ring 12, the opposite sides of the first lifting sleeve block 7 and the second lifting sleeve block 10 are both rotationally connected with a rotating mounting shaft 13, the middle of the two rotating mounting shafts 13 is provided with a turnover mounting ring 14, the outer surface of the turnover mounting ring 14 is fixedly connected with four mounting lugs 15 arranged in an annular array, the opposite ends of the two rotating mounting shafts 13 are respectively fixedly connected with corresponding mounting lugs 15, and the inner wall of the lifting linkage ring 12 is provided with a second power assembly for driving the rotating mounting shaft 13 to rotate, the second power assembly comprises a third servo motor 23 fixedly connected to the inner wall of the lifting linkage ring 12, the output shaft of the third servo motor 23 is fixedly connected with a third belt pulley, the outer surface of the rotating mounting shaft 13 is fixedly connected with a fourth belt pulley, the third belt pulley and the fourth belt pulley are drivingly connected through a second belt, the third servo motor 23 is started, the output shaft of the third servo motor 23 drives the third belt pulley to rotate, so that the rotating mounting shaft 13 drives the turnover mounting ring 14 to overturn, and the rotating mounting ring 18 drives the engine turbine blade to overturn;

[0034] The opposite side of the two third lifting sleeve blocks 11 is provided with a limiting assembly, the limiting assembly comprises a first driving cylinder 16 fixedly connected to the outer wall of the third lifting sleeve block 11, the piston end of the first driving cylinder 16 is fixedly connected with a limiting protruding rod 17, the end of the limiting protruding rod 17 away from the first driving cylinder 16 is clamped with a corresponding mounting protruding block 15, a clamping hole matched with the mounting protruding block 15 is formed in the side wall of the mounting protruding block 15, the first driving cylinder 16 is started to clamp the limiting protruding rod 17 with the mounting protruding block 15, thereby limiting the overturning mounting ring 14 and increasing the stability of the overturning mounting ring 14;

[0035] The upper surface of the overturning mounting ring 14 is rotatably connected with a rotating mounting ring 18, and the outer side wall of the overturning mounting ring 14 is provided with a third power assembly for driving the rotating mounting ring 18 to rotate, the third power assembly comprises a mounting fixed seat 20 fixedly connected to the outer side wall of the overturning mounting ring 14, the upper surface of the mounting fixed seat 20 is fixedly connected with a second servo motor 21, the output shaft of the second servo motor 21 is fixedly connected with a rotating gear 22, the outer side wall of the rotating mounting ring 18 is fixedly connected with a rotating outer gear ring 19, the rotating gear 22 is meshingly connected with the rotating outer gear ring 19, the second servo motor 21 is started, the output shaft of the second servo motor 21 drives the rotating gear 22 to rotate, the rotating gear 22 drives the rotating outer gear ring 19 to rotate, the rotating outer gear ring 19 drives the rotating mounting ring 18 to rotate, and the rotating mounting ring 18 drives the engine turbine blade to rotate and spray;

[0036] The upper surface of the rotating mounting ring 18 is provided with four arc-shaped mounting grooves 35 arranged in an annular array, a moving mounting block 24 is slidably connected in the arc-shaped mounting groove 35, the lower surface of the moving mounting block 24 is fixedly connected with a sliding block, the sliding block is slidably connected in the arc-shaped mounting groove 35, and the upper surface of the rotating mounting ring 18 is provided with a fourth power assembly for driving the moving mounting block 24 to move, the fourth power assembly comprises a second driving cylinder 25 rotatably connected to the upper surface of the rotating mounting ring 18, the piston end of the second driving cylinder 25 is fixedly connected with a connecting shaft, the end of the connecting shaft away from the second driving cylinder 25 is rotatably connected with a connecting rectangular block 26, the connecting rectangular block 26 is fixedly connected to the side wall of the moving mounting block 24, and the second driving cylinder 25 is started, the piston end of the second driving cylinder 25 drives the connecting rectangular block 26 to move through the connecting shaft, and the connecting rectangular block 26 drives the moving mounting block 24 to move in the arc-shaped mounting groove 35;

[0037] The inside of the moving mounting block 24 is internally mounted with a clamping assembly, which comprises a third drive cylinder 27 fixedly connected to the inside of the moving mounting block 24, the piston end of the third drive cylinder 27 is fixedly connected with a connecting fixed disc 28, the side wall of the connecting fixed disc 28 is fixedly connected with a fourth servo motor 29, the output shaft of the fourth servo motor 29 is fixedly connected with a rectangular mounting plate 30, the side wall of the rectangular mounting plate 30 is slidably connected with two inclined leaf clamping plates 31, the opposite side of each of the two leaf clamping plates 31 is fixedly connected with a fixed soft pad plate 32, the side wall of the rectangular mounting plate 30 is fixedly connected with two mounting rectangular blocks 33, the side wall of each of the two mounting rectangular blocks 33 is fixedly connected with a fourth drive cylinder 34, the piston end of each of the fourth drive cylinders 34 is fixedly connected with a corresponding leaf clamping plate 31, the third drive cylinder 27 is started, the piston end of the third drive cylinder 27 moves with the connecting fixed disc 28, so that the fourth servo motor 29 moves with the two leaf clamping plates 31 through the rectangular mounting plate 30 to approach the curved blade, so that the two leaf clamping plates 31 are located on both sides of the curved blade, and then the fourth drive cylinder 34 is started, the piston end of the fourth drive cylinder 34 moves with the leaf clamping plate 31, so that the two leaf clamping plates 31 approach each other to clamp the curved blade.

[0038] Working principle:

[0039] In use, the central hole of the engine turbine blade is inserted into the through positioning column 4, and the engine turbine blade is placed on the limiting mounting disc 5.

[0040] The first servo motor 8 is started, the output shaft of the first servo motor 8 rotates with the first belt pulley, so that the threaded rotating rod 6 rotates, so that the first lifting sleeve block 7, the second lifting sleeve block 10 and the third lifting sleeve block 11 descend with the turnover mounting ring 14, the turnover mounting ring 14 descends with the rotating mounting ring 18, so that the two leaf clamping plates 31 are aligned with the curved blade, then the third drive cylinder 27 is started, the piston end of the third drive cylinder 27 moves with the connecting fixed disc 28, so that the fourth servo motor 29 moves with the two leaf clamping plates 31 through the rectangular mounting plate 30 to approach the curved blade, so that the two leaf clamping plates 31 are located on both sides of the curved blade, then the fourth drive cylinder 34 is started, the piston end of the fourth drive cylinder 34 moves with the leaf clamping plate 31, so that the two leaf clamping plates 31 approach each other to clamp the curved blade, then the first servo motor 8 is reversed, and the engine turbine blade rises, then the engine turbine blade is subjected to laser shot blasting treatment through the equipment, and the second servo motor 21 is started, the output shaft of the second servo motor 21 rotates with the rotating gear 22, the rotating gear 22 rotates with the rotating outer gear ring 19, the rotating outer gear ring 19 rotates with the rotating mounting ring 18, and the rotating mounting ring 18 rotates with the engine turbine blade to perform rotary shot blasting;

[0041] After the shot blasting, the two sets of oppositely arranged blade clamping plates 31 are loosened from the curved blades, the third drive cylinder 27 brings the blade clamping plate 31 back to the original position, and then the second drive cylinder 25 is started, the piston end of the second drive cylinder 25 moves the connecting rectangular block 26 through the connecting shaft, the connecting rectangular block 26 moves the moving mounting block 24 in the arc-shaped mounting groove 35, and the blade clamping plate 31 is moved to the curved blade that has been shot blasted, and clamping is performed again through the blade clamping plate 31. In the above manner, the other two sets of blade clamping plates 31 are moved, and the curved blades that have not been treated are treated by the device.

[0042] After one side of the engine turbine blade is shot blasted, the two first drive cylinders 16 are started, the piston end of the first drive cylinder 16 retracts the limiting protruding rod 17, so that the limiting protruding rod 17 is separated from the mounting protruding block 15 (since the lifting linkage ring 12 is arranged, when the limiting protruding rod 17 is separated from the mounting protruding block 15, the two third lifting sleeve blocks 11 will not fall off), then the third servo motor 23 is started, the output shaft of the third servo motor 23 rotates the third belt pulley, so that the rotating mounting shaft 13 rotates the turnover mounting ring 14, and the rotating mounting ring 18 rotates the engine turbine blade. After the turnover is completed, the first drive cylinder 16 is started, so that the limiting protruding rod 17 is clamped with the mounting protruding block 15. In the above manner, the other side of the engine turbine blade is treated by laser shot blasting.

[0043] It should be noted that in this document, the terms such as first and second are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device. Without more limitations, the element defined by the statement "including a reference structure" does not exclude the presence of other identical elements in the process, method, article or device including the element.

[0044] Although embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and alterations can be made thereto without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An annular fixture for laser peening of aeroengine turbine blade, comprising an annular mounting table (1), characterized in that: The inner wall of the annular mounting table (1) is fixedly connected with a cross fixed seat (2), the middle of the upper surface of the cross fixed seat (2) is connected with a positioning placing assembly, the upper surface of the annular mounting table (1) is rotatably connected with a threaded rotating rod (6), the outer surface of the threaded rotating rod (6) is threadedly connected with a first lifting sleeve block (7), the upper surface of the cross fixed seat (2) is provided with a first power assembly for driving the threaded rotating rod (6) to rotate, the upper surface of the annular mounting table (1) is fixedly connected with three vertical guide vertical rods (9), the outer surface of one of the vertical guide vertical rods (9) is sleeved with a second lifting sleeve block (10), the outer surfaces of the other two vertical guide vertical rods (9) are both sleeved with a third lifting sleeve block (11), the outer sides of the first lifting sleeve block (7), the second lifting sleeve block (10) and the third lifting sleeve block (11) are fixedly connected with a lifting linkage ring (12), the sides opposite to the first lifting sleeve block (7) and the second lifting sleeve block (10) are both rotatably connected with a rotating mounting shaft (13), the middle of the two rotating mounting shafts (13) is provided with a turnover mounting ring (14), the outer surface of the turnover mounting ring (14) is fixedly connected with four mounting lugs (15) arranged in an annular array, the ends opposite to the two rotating mounting shafts (13) are respectively fixedly connected with corresponding mounting lugs (15), the inner wall of the lifting linkage ring (12) is provided with a second power assembly for driving the rotating mounting shaft (13) to rotate, the sides opposite to the two third lifting sleeve blocks (11) are both provided with a limiting assembly, the upper surface of the turnover mounting ring (14) is rotatably connected with a rotating mounting ring (18), the outer side wall of the turnover mounting ring (14) is provided with a third power assembly for driving the rotating mounting ring (18) to rotate, the upper surface of the rotating mounting ring (18) is provided with four arc-shaped mounting grooves (35) arranged in an annular array, the inside of the arc-shaped mounting groove (35) is slidably connected with a moving mounting block (24), the upper surface of the rotating mounting ring (18) is provided with a fourth power assembly for driving the moving mounting block (24) to move, the inside of the moving mounting block (24) is provided with a clamping assembly.

2. The annular fixture for laser peening of turbine blades of an aeroengine according to claim 1, characterized in that: The positioning placing assembly comprises a vertical fixed column (3) fixedly connected to the upper surface of the cross fixed seat (2), and a penetrating positioning column (4) fixedly connected to the top of the vertical fixed column (3).

3. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The first power assembly comprises a first servo motor (8) fixedly connected to the upper surface of the cross fixed seat (2), a first pulley fixedly connected to the output shaft of the first servo motor (8), and a second pulley fixedly connected to the outer surface of the threaded rotating rod (6), and the first pulley and the second pulley are drivingly connected through a first belt.

4. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The second power assembly comprises a third servo motor (23) fixedly connected to the inner wall of the lifting linkage ring (12), the output shaft of the third servo motor (23) is fixedly connected with a third belt pulley, the outer surface of the rotary mounting shaft (13) is fixedly connected with a fourth belt pulley, and the third belt pulley and the fourth belt pulley are transmissionally connected through a second belt.

5. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The limiting assembly comprises a first drive cylinder (16) fixedly connected to the outer wall of the third lifting sleeve block (11), the piston end of the first drive cylinder (16) is fixedly connected with a limiting protruding rod (17), one end of the limiting protruding rod (17) away from the first drive cylinder (16) is clamped with a corresponding mounting protruding block (15), and a clamping hole matched with the mounting protruding block (15) is formed in the side wall of the mounting protruding block (15).

6. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The third power assembly comprises a mounting fixed seat (20) fixedly connected to the outer side wall of the overturning mounting ring (14), the upper surface of the mounting fixed seat (20) is fixedly connected with a second servo motor (21), the output shaft of the second servo motor (21) is fixedly connected with a rotary gear (22), the outer side wall of the rotary mounting ring (18) is fixedly connected with a rotary outer gear ring (19), and the rotary gear (22) is meshingly connected with the rotary outer gear ring (19).

7. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The fourth power assembly comprises a second drive cylinder (25) rotationally connected to the upper surface of the rotary mounting ring (18), the piston end of the second drive cylinder (25) is fixedly connected with a connecting shaft, one end of the connecting shaft away from the second drive cylinder (25) is rotationally connected with a connecting rectangular block (26), and the connecting rectangular block (26) is fixedly connected to the side wall of a moving mounting block (24).

8. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The clamping assembly comprises a third drive cylinder (27) fixedly connected to the inside of the moving mounting block (24), the piston end of the third drive cylinder (27) is fixedly connected with a connecting fixed disc (28), the side wall of the connecting fixed disc (28) is fixedly connected with a fourth servo motor (29), the output shaft of the fourth servo motor (29) is fixedly connected with a rectangular mounting plate (30), two inclined blade clamping plates (31) are slidingly connected to the side wall of the rectangular mounting plate (30), the opposite side of each of the two blade clamping plates (31) is fixedly connected with a fixed soft pad plate (32), two mounting rectangular blocks (33) are fixedly connected to the side wall of the rectangular mounting plate (30), the side wall of each of the mounting rectangular blocks (33) is fixedly connected with a fourth drive cylinder (34), and the piston end of the fourth drive cylinder (34) is fixedly connected with a corresponding blade clamping plate (31).

9. The annular fixture for laser peening of turbine blades of a gas turbine engine of claim 1, wherein: The lower surface of the moving mounting block (24) is fixedly connected with a sliding block, and the sliding block is slidingly connected to the inside of the arc-shaped mounting groove (35).

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