Annular clamp for laser peening of turbine blade of aero-engine

Abstract

The invention provides an annular clamp for laser peening of an aero-engine turbine blade, and relates to the technical field of turbine blade machining. The annular clamp for laser peening of the aero-engine turbine blade comprises an annular mounting table, a cross-shaped fixing 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-shaped fixing seat, and a threaded rotating rod is rotationally connected to the upper surface of the annular mounting table. According to the device, a third driving air cylinder is started, the piston end of the third driving air cylinder drives a connecting and fixing disc to move, a fourth servo motor drives two blade clamping plates to get close to a curved blade through a rectangular mounting plate, the two blade clamping plates are located on the two sides of the curved blade, and by starting the fourth servo motor, the curved blade can be clamped by the two blade clamping plates. And an output shaft of a fourth servo motor drives a rectangular mounting plate to rotate, the rectangular mounting plate drives two blade clamping plates to rotate, the angle of the two blade clamping plates can be changed, the device is suitable for different turbine blades, and the adaptation degree is high.

Description

Technical Field

[0001] This invention relates to the field of turbine blade processing technology, specifically to a ring-shaped fixture for laser shot peening of aero-engine turbine blades. Background Technology

[0002] Laser peening is a surface treatment method that uses high-energy shock waves induced by strong pulsed lasers to form a compressive stress layer on the surface of parts, thereby effectively improving their service life. This method is commonly used in high-precision components such as aero-engine blades and automotive precision gears. With social progress and the rapid growth of my country's industrial level, automated laser peening has become a hot topic in the development of peening technology.

[0003] Fixtures are an important component of laser peening equipment. Currently, most laser peening fixtures are mechanical fixtures. Due to the highly irregular curvature of engine turbine blades, traditional fixtures are difficult to adapt to different curved turbine blades during the clamping process, which can easily lead to insecure clamping or even damage to the blades. At the same time, after clamping, the clamped part cannot be laser peened, nor can it be flipped over. It often needs to be removed and re-clamped, resulting in low processing efficiency. Summary of the Invention

[0004] (a) Technical problems to be solved To address the shortcomings of existing technologies, this invention provides a ring-shaped fixture for laser shot peening of aero-engine turbine blades, which solves the problems of traditional fixtures being difficult to apply to turbine blades with different curved surfaces and having low processing efficiency.

[0005] (II) Technical Solution To achieve the above objectives, the present invention provides the following technical solution: an annular fixture for laser shot peening of aero-engine turbine blades, comprising an annular mounting platform, a cross-shaped fixing seat fixedly connected to the inner wall of the annular mounting platform, a positioning and placement component connected to the middle of the upper surface of the cross-shaped fixing seat, a threaded rotating rod rotatably connected to the upper surface of the annular mounting platform, a first lifting sleeve block threadedly connected to the outer surface of the threaded rotating rod, a first power component for driving the threaded rotating rod to rotate mounted on the upper surface of the cross-shaped fixing seat, three vertical guide rods fixedly connected to the upper surface of the annular mounting platform, a second lifting sleeve block sleeved on the outer surface of one of the vertical guide rods, and a third lifting sleeve block sleeved on the outer surfaces of the other two vertical guide rods, with a lifting linkage ring fixedly connected to the outer sides of the first, second, and third lifting sleeve blocks, and the first and second lifting sleeve blocks being connected to each other. Each of the two rotating mounting blocks is rotatably connected to a rotating mounting shaft on one side. A flip mounting ring is provided between the two rotating mounting shafts. Four mounting protrusions arranged in a circular array are fixedly connected to the outer surface of the flip mounting ring. The opposite ends of the two rotating mounting shafts are respectively fixedly connected to the corresponding mounting protrusions. A second power assembly for driving the rotating mounting shafts to rotate is installed on the inner wall of the lifting linkage ring. Limiting components are installed on the opposite sides of the two third lifting sleeve blocks. A rotating mounting ring is rotatably connected to the upper surface of the flip mounting ring. A third power assembly for driving the rotating mounting ring to rotate is installed on the outer wall of the flip mounting ring. Four arc-shaped mounting grooves arranged in a circular array are opened on the upper surface of the rotating mounting ring. A movable mounting block is slidably connected inside the arc-shaped mounting groove. A fourth power assembly for driving the movable mounting block to move is installed on the upper surface of the rotating mounting ring. A clamping component is installed inside the movable mounting block.

[0006] Preferably, the positioning and placement assembly includes a vertical fixing column fixedly connected to the upper surface of the cross fixing seat, a through positioning column fixedly connected to the top of the vertical fixing column, and a limit mounting disc fixedly connected to the outer surface of the through positioning column.

[0007] Preferably, the first power assembly includes a first servo motor fixedly connected to the upper surface of the cross-shaped fixed base. The output shaft of the first servo motor is fixedly connected to a first pulley, and the outer surface of the threaded rotating rod is fixedly connected to a second pulley. The first pulley and the second pulley are connected by a first belt drive. When the first servo motor is started, the output shaft of the first servo motor rotates the first pulley, causing the threaded rotating rod to rotate. This causes the first lifting sleeve block, the second lifting sleeve block, and the third lifting sleeve block to descend with the flip-mounted mounting ring, and the flip-mounted mounting ring to descend with the rotating mounting ring.

[0008] Preferably, the second power assembly includes 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 to a third pulley, and the outer surface of the rotary mounting shaft is fixedly connected to a fourth pulley. The third pulley and the fourth pulley are connected by a second belt drive. When the third servo motor is started, the output shaft of the third servo motor rotates the third pulley, causing the rotary mounting shaft to rotate the rotating mounting ring, and the rotating mounting ring to rotate the engine turbine blades.

[0009] Preferably, the limiting component includes a first driving cylinder fixedly connected to the outer wall of the third lifting sleeve block. A limiting protrusion is fixedly connected to the piston end of the first driving cylinder. The end of the limiting protrusion away from the first driving cylinder is engaged with a corresponding mounting protrusion. A engaging hole adapted to the mounting protrusion is provided on the side wall of the mounting protrusion.

[0010] Preferably, the third power assembly includes a mounting base fixedly connected to the outer wall of the rotating mounting ring. A second servo motor is fixedly connected to the upper surface of the mounting base. A rotating gear is fixedly connected to the output shaft of the second servo motor. A rotating external gear ring is fixedly connected to the outer wall of the rotating mounting ring. The rotating gear meshes with the rotating external gear ring. When the second servo motor is started, the output shaft of the second servo motor rotates the rotating gear, which in turn rotates the rotating external gear ring. The rotating external gear ring then rotates the rotating mounting ring, and the rotating mounting ring rotates the engine turbine blades for rotating shot peening.

[0011] Preferably, the fourth power assembly includes a second drive cylinder rotatably connected to the upper surface of the rotary mounting ring. The piston end of the second drive cylinder is fixedly connected to a connecting shaft. The end of the connecting shaft away from the second drive cylinder is rotatably connected to a connecting rectangular block. The connecting rectangular block is fixedly connected to the side wall of the movable mounting block. When the second drive cylinder is activated, the piston end of the second drive cylinder moves the connecting rectangular block through the connecting shaft. The connecting rectangular block moves the movable mounting block in the arc-shaped mounting groove, allowing the blade clamping plate to move to the curved blade that has been shot-peened.

[0012] Preferably, the clamping assembly includes a third drive cylinder fixedly connected inside the movable mounting block. A connecting mounting plate is fixedly connected to the piston end of the third drive cylinder. A fourth servo motor is fixedly connected to the side wall of the connecting mounting plate. A rectangular mounting plate is fixedly connected to the output shaft of the fourth servo motor. Two inclined blade clamping plates are slidably connected to the side wall of the rectangular mounting plate. A fixing pad is fixedly connected to each of the two blade clamping plates on opposite sides. Two mounting rectangular blocks are fixedly connected to the side wall of the rectangular mounting plate. A fourth drive cylinder is fixedly connected to the side wall of each mounting rectangular block. The piston end of the fourth drive cylinder is fixedly connected to the corresponding blade clamping plate. When the third drive cylinder is activated, its piston end moves the connecting mounting plate, causing the fourth servo motor to move the two blade clamping plates closer to the curved blade via the rectangular mounting plate, positioning the two blade clamping plates on either side of the curved blade. Activating the fourth servo motor causes its output shaft to rotate the rectangular mounting plate, which in turn rotates the two blade clamping plates.

[0013] Preferably, a sliding block is fixedly connected to the lower surface of the movable mounting block, and the sliding block is slidably connected inside the arc-shaped mounting groove.

[0014] (III) Beneficial Effects This invention provides a ring-shaped fixture for laser shot peening of aero-engine turbine blades. It has the following beneficial effects: 1. In this invention, the third drive cylinder is activated, and the piston end of the third drive cylinder moves with the connecting fixing plate, so that the fourth servo motor moves with the two blade clamping plates through the rectangular mounting plate toward the curved blade, so that the two blade clamping plates are located on both sides of the curved blade. By activating the fourth servo motor, 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, which can change the angle of the two blade clamping plates, making it suitable for different turbine blades and highly adaptable.

[0015] 2. In this invention, the two sets of opposing blade clamping plates first release the curved blades. The third drive cylinder then resets the blade clamping plates. Next, the second drive cylinder is activated. The piston end of the second drive cylinder moves the connecting rectangular block via the connecting shaft. The connecting rectangular block moves the movable mounting block in the arc-shaped mounting groove, allowing the blade clamping plates to move to the curved blades that have already been shot-peened. The blade clamping plates then clamp the blades again. Following the same method, the other two sets of blade clamping plates are moved. The equipment then performs laser shot peening on the untreated curved blades, resulting in a more comprehensive treatment.

[0016] 3. In this invention, two first drive cylinders are first activated. The piston end of the first drive cylinder retracts with the limiting protrusion, causing the limiting protrusion to separate from the mounting protrusion. Then, the third servo motor is activated. The output shaft of the third servo motor rotates with the third pulley, causing the rotating mounting shaft to rotate with the flipping mounting ring. The rotating mounting ring rotates the engine turbine blades. After the rotation is completed, the first drive cylinder is activated, causing the limiting protrusion to engage with the mounting protrusion. In the above manner, the other side of the engine turbine blades is laser shot peened, resulting in high processing efficiency.

[0017] 4. In this invention, the second servo motor is started, the output shaft of the second servo motor drives the rotating gear to rotate, the rotating gear drives the rotating external gear ring to rotate, the rotating external gear ring drives the rotating mounting ring to rotate, and the rotating mounting ring drives the engine turbine blades to rotate for shot peening. Attached Figure Description

[0018] Figure 1 A three-dimensional structural schematic diagram of a ring-shaped fixture for laser shot peening of aero-engine turbine blades provided by the present invention; Figure 2 A top view of a ring-shaped fixture for laser shot peening of aero-engine turbine blades provided by the present invention; Figure 3 A schematic diagram of the rotating mounting ring structure of an annular clamp for laser shot peening of aero-engine turbine blades provided by the present invention; Figure 4 This invention provides a ring-shaped fixture for laser shot peening of aero-engine turbine blades. Figure 3 Enlarged view of point A in the middle; Figure 5 A schematic diagram of the movable mounting block structure of an annular clamp for laser shot peening of aero-engine turbine blades provided by the present invention; Figure 6 This invention provides a schematic diagram of the blade clamping plate structure of an annular fixture for laser shot peening of aero-engine turbine blades.

[0019] 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

[0020] 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.

[0021] Example: 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. A threaded rotating rod 6 is rotatably connected to the upper surface of the annular mounting platform 1. A first lifting sleeve block 7 is threadedly connected to the outer surface of the threaded rotating rod 6. A first power assembly for driving the threaded rotating rod 6 to rotate is mounted on the upper surface of the cross-shaped fixing seat 2. The first power assembly includes a first servo motor 8 fixedly connected to the upper surface of the cross-shaped fixing seat 2. A first pulley is fixedly connected to the output shaft of the first servo motor 8. A second pulley is fixedly connected to the outer surface of the threaded rotating rod 6. The first pulley and the second pulley are connected by a first belt drive. When the first servo motor 8 is started, the output shaft of the first servo motor 8 drives the first pulley to rotate, causing the threaded rotating rod 6 to rotate. This causes the first lifting sleeve block 7, the second lifting sleeve block 10, and the third lifting sleeve block 11 to descend with the flipping mounting ring 14. The flipping mounting ring 14 then descends with the rotating mounting ring 18. Three vertical guide rods 9 are fixedly connected to the upper surface of the annular mounting platform 1. A second lifting sleeve block 10 is fitted on the outer surface of one of the vertical guide rods 9, and a third lifting sleeve block 11 is fitted on the outer surface of the other two vertical guide rods 9. A lifting linkage ring 12 is fixedly connected to the outer sides of the first lifting sleeve block 7, the second lifting sleeve block 10, and the third lifting sleeve block 11. The lifting linkage ring 12 allows the first lifting sleeve block 7, the second lifting sleeve block 10, and the third lifting sleeve block 11 to rise and fall synchronously. A rotating mounting shaft 13 is rotatably connected to the opposite side of the first lifting sleeve block 7 and the second lifting sleeve block 10. A flip mounting ring 14 is provided in the middle of the two rotating mounting shafts 13. Four ring-shaped mounting rings are fixedly connected to the outer surface of the flip mounting ring 14. The mounting protrusions 15 are arranged in a row. The opposite ends of the two rotating mounting shafts 13 are respectively fixedly connected to the corresponding mounting protrusions 15. A second power assembly for driving the rotating mounting shafts 13 to rotate is installed on the inner wall of the lifting linkage ring 12. The second power assembly includes 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 to a third pulley. A fourth pulley is fixedly connected to the outer surface of the rotating mounting shaft 13. The third pulley and the fourth pulley are connected by a second belt drive. When the third servo motor 23 is started, the output shaft of the third servo motor 23 drives the third pulley to rotate, so that the rotating mounting shaft 13 drives the flip mounting ring 14 to flip. The rotating mounting ring 18 drives the engine turbine blades to flip. Limiting components are installed on opposite sides of the two third lifting sleeve blocks 11. The limiting components include a first driving cylinder 16 fixedly connected to the outer wall of the third lifting sleeve block 11. A limiting protrusion 17 is fixedly connected to the piston end of the first driving cylinder 16. The end of the limiting protrusion 17 away from the first driving cylinder 16 is engaged with the corresponding mounting protrusion 15. The side wall of the mounting protrusion 15 is provided with a locking hole adapted to the mounting protrusion 15. When the first driving cylinder 16 is activated, the limiting protrusion 17 is engaged with the mounting protrusion 15, thereby limiting the flip mounting ring 14 and increasing the stability of the flip mounting ring 14. A rotating mounting ring 18 is rotatably connected to the upper surface of the flip mounting ring 14. A third power assembly for driving the rotating mounting ring 18 to rotate is installed on the outer wall of the flip mounting ring 14. The third power assembly includes a mounting base 20 fixedly connected to the outer wall of the flip mounting ring 14. A second servo motor 21 is fixedly connected to the upper surface of the mounting base 20. A rotating gear 22 is fixedly connected to the output shaft of the second servo motor 21. A rotating external gear ring 19 is fixedly connected to the outer wall of the rotating mounting ring 18. The rotating gear 22 meshes with the rotating external gear ring 19. When 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 external gear ring 19 to rotate. The rotating external gear ring 19 drives the rotating mounting ring 18 to rotate. The rotating mounting ring 18 drives the engine turbine blades to perform rotating shot peening. The upper surface of the rotating mounting ring 18 is provided with four arc-shaped mounting grooves 35 arranged in a circular array. A movable mounting block 24 is slidably connected inside the arc-shaped mounting groove 35. A sliding block is fixedly connected to the lower surface of the movable mounting block 24. The sliding block is slidably connected inside the arc-shaped mounting groove 35. A fourth power assembly for driving the movable mounting block 24 to move is installed on the upper surface of the rotating mounting ring 18. The fourth power assembly includes a second driving cylinder 25 rotatably connected to the upper surface of the rotating mounting ring 18. A connecting shaft is fixedly connected to the piston end of the second driving cylinder 25. A connecting rectangular block 26 is rotatably connected to the end of the connecting shaft away from the second driving cylinder 25. The connecting rectangular block 26 is fixedly connected to the side wall of the movable mounting block 24. When the second driving cylinder 25 is activated, the piston end of the second driving cylinder 25 moves the connecting rectangular block 26 through the connecting shaft. The connecting rectangular block 26 moves the movable mounting block 24 in the arc-shaped mounting groove 35. The movable mounting block 24 houses a clamping assembly, which includes a third drive cylinder 27 fixedly connected inside the movable mounting block 24. A connecting mounting plate 28 is fixedly connected to the piston end of the third drive cylinder 27. A fourth servo motor 29 is fixedly connected to the side wall of the connecting mounting plate 28. A rectangular mounting plate 30 is fixedly connected to the output shaft of the fourth servo motor 29. Two inclined blade clamping plates 31 are slidably connected to the side wall of the rectangular mounting plate 30. A fixing soft pad 32 is fixedly connected to the opposite side of each of the two blade clamping plates 31. Two mounting rectangular blocks 33 are fixedly connected to the side wall of the rectangular mounting plate 30. A fourth drive cylinder 34 is fixedly connected to the side wall of the mounting rectangular block 33. The piston end of the fourth drive cylinder 34 is fixedly connected to the corresponding blade clamping plate 31. The third drive cylinder 27 is started, and the piston end of the third drive cylinder 27 moves with the connecting fixing plate 28, so that the fourth servo motor 29 moves the two blade clamping plates 31 closer to the curved blade through the rectangular mounting plate 30, so that the two blade clamping plates 31 are located on both sides of the curved blade. Then the fourth drive cylinder 34 is started again, and the piston end of the fourth drive cylinder 34 moves with the blade clamping plate 31, so that the two blade clamping plates 31 move closer to each other and clamp the curved blade.

[0022] Working principle: When in use, insert the center hole of the engine turbine blade into the through positioning post 4, and place the engine turbine blade on the limiting mounting disc 5. The first servo motor 8 is started, and its output shaft rotates the first pulley, causing the threaded rotating rod 6 to rotate. This causes the first lifting sleeve 7, the second lifting sleeve 10, and the third lifting sleeve 11 to descend along with the flipping mounting ring 14. The flipping mounting ring 14, along with the rotating mounting ring 18, descends, aligning the two blade clamping plates 31 with the curved blade. Then, the third drive cylinder 27 is started, and its piston end moves along with the connecting fixing plate 28. This causes the fourth servo motor 29 to move the two blade clamping plates 31 closer to the curved blade via the rectangular mounting plate 30, positioning the two blade clamping plates 31 within the curved blade. The two sides of the curved blade are then activated, and the fourth drive cylinder 34 is started. The piston end of the fourth drive cylinder 34 moves the blade clamping plate 31, so that the two blade clamping plates 31 move closer to each other to clamp the curved blade. Then the first servo motor 8 is started to reverse, which raises the engine turbine blade. Then the engine turbine blade is laser shot peened by the equipment. The second servo motor 21 is started, and the output shaft of the second servo motor 21 rotates the rotating gear 22. The rotating gear 22 rotates the rotating external gear ring 19. The rotating external gear ring 19 rotates the rotating mounting ring 18. The rotating mounting ring 18 rotates the engine turbine blade for rotating shot peening. After shot peening, the two sets of oppositely positioned blade clamping plates 31 are first released from the curved blades. The third drive cylinder 27 resets the blade clamping plates 31. 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, allowing the blade clamping plates 31 to move to the curved blades that have been shot peened. The blade clamping plates 31 are then clamped again. The other two sets of blade clamping plates 31 are moved in the same way. The equipment then performs laser shot peening on the untreated curved blades. After shot peening one side of the engine turbine blade, the two first drive cylinders 16 are started. The piston end of the first drive cylinder 16 retracts with the limiting protrusion 17, so that the limiting protrusion 17 separates from the mounting protrusion 15 (because of the lifting linkage ring 12, the two third lifting sleeves 11 will not fall off when the limiting protrusion 17 separates from the mounting protrusion 15). Then the third servo motor 23 is started. The output shaft of the third servo motor 23 rotates with the third pulley, so that the rotating mounting shaft 13 rotates with the flipping mounting ring 14. The rotating mounting ring 18 rotates with the engine turbine blade. After the rotation is completed, the first drive cylinder 16 is started, so that the limiting protrusion 17 and the mounting protrusion 15 are engaged. The other side of the engine turbine blade is laser shot peened in the same way.

[0023] It should be noted that, in this document, relational 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. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising a reference structure" does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0024] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A ring-shaped fixture for laser shot peening of turbine blades of aero-engines, comprising a ring-shaped mounting platform (1), characterized in that: The inner wall of the annular mounting platform (1) is fixedly connected to a cross-shaped fixing seat (2). A positioning and placement component is connected to the middle of the upper surface of the cross-shaped fixing seat (2). A threaded rotating rod (6) is rotatably connected to the upper surface of the annular mounting platform (1). A first lifting sleeve block (7) is threadedly connected to the outer surface of the threaded rotating rod (6). A first power component for driving the threaded rotating rod (6) to rotate is installed on the upper surface of the cross-shaped fixing seat (2). Three vertical guide rods (9) are fixedly connected to the upper surface of the annular mounting platform (1). A second lifting sleeve block (10) is sleeved on the outer surface of one of the vertical guide rods (9). A third lifting sleeve block (11) is sleeved on the outer surface of the other two vertical guide rods (9). A lifting linkage ring (12) is fixedly connected to the outer sides of the first lifting sleeve block (7), the second lifting sleeve block (10), and the third lifting sleeve block (11). A rotating mounting shaft (13) is rotatably connected to the opposite side of the first lifting sleeve block (7) and the second lifting sleeve block (10). The two rotating mounting shafts (13) A flip-mounting ring (14) is provided in the middle. Four mounting protrusions (15) arranged in a circular array are fixedly connected to the outer surface of the flip-mounting ring (14). The opposite ends of the two rotating mounting shafts (13) are respectively fixedly connected to the corresponding mounting protrusions (15). A second power component for driving the rotating mounting shafts (13) to rotate is installed on the inner wall of the lifting linkage ring (12). Limiting components are installed on the opposite sides of the two third lifting sleeves (11). The upper surface of the flip-mounting ring (14) is rotatably connected to... There is a rotating mounting ring (18). The outer wall of the flip mounting ring (14) is equipped with a third power component that drives 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 a ring array. The interior of the arc-shaped mounting grooves (35) is slidably connected to a movable mounting block (24). The upper surface of the rotating mounting ring (18) is equipped with a fourth power component that drives the movable mounting block (24) to move. The interior of the movable mounting block (24) is equipped with a clamping component.

2. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The positioning and placement assembly includes a vertical fixing column (3) fixedly connected to the upper surface of the cross fixing base (2), a through positioning column (4) fixedly connected to the top of the vertical fixing column (3), and a limit mounting disc (5) fixedly connected to the outer surface of the through positioning column (4).

3. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The first power assembly includes a first servo motor (8) fixedly connected to the upper surface of the cross-shaped fixed base (2), the output shaft of the first servo motor (8) is fixedly connected to a first pulley, and the outer surface of the threaded rotating rod (6) is fixedly connected to a second pulley. The first pulley and the second pulley are connected by a first belt drive.

4. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The second power assembly includes 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 to a third pulley, and the outer surface of the rotary mounting shaft (13) is fixedly connected to a fourth pulley. The third pulley and the fourth pulley are connected by a second belt drive.

5. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The limiting component includes a first driving cylinder (16) fixedly connected to the outer wall of the third lifting sleeve (11). The piston end of the first driving cylinder (16) is fixedly connected to a limiting protrusion (17). The end of the limiting protrusion (17) away from the first driving cylinder (16) is engaged with a corresponding mounting protrusion (15). The side wall of the mounting protrusion (15) is provided with a engagement hole that matches the mounting protrusion (15).

6. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The third power assembly includes a mounting base (20) fixedly connected to the outer wall of the flip mounting ring (14). A second servo motor (21) is fixedly connected to the upper surface of the mounting base (20). A rotary gear (22) is fixedly connected to the output shaft of the second servo motor (21). A rotary external gear ring (19) is fixedly connected to the outer wall of the rotary mounting ring (18). The rotary gear (22) meshes with the rotary external gear ring (19).

7. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The fourth power assembly includes a second drive cylinder (25) rotatably connected to the upper surface of the rotating mounting ring (18). The piston end of the second drive cylinder (25) is fixedly connected to a connecting shaft. The end of the connecting shaft away from the second drive cylinder (25) is rotatably connected to a connecting rectangular block (26). The connecting rectangular block (26) is fixedly connected to the side wall of the movable mounting block (24).

8. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: The clamping assembly includes a third drive cylinder (27) fixedly connected inside the movable mounting block (24). The piston end of the third drive cylinder (27) is fixedly connected to a connecting fixing plate (28). A fourth servo motor (29) is fixedly connected to the side wall of the connecting fixing plate (28). The output shaft of the fourth servo motor (29) is fixedly connected to a rectangular mounting plate (30). Two inclined blade clamping plates (31) are slidably connected to the side wall of the rectangular mounting plate (30). A fixing soft pad (32) is fixedly connected to the opposite side of each of the two blade clamping plates (31). Two mounting rectangular blocks (33) are fixedly connected to the side wall of the rectangular mounting plate (30). A fourth drive cylinder (34) is fixedly connected to the side wall of the mounting rectangular block (33). The piston end of the fourth drive cylinder (34) is fixedly connected to the corresponding blade clamping plate (31).

9. The annular fixture for laser shot peening of aero-engine turbine blades according to claim 1, characterized in that: A sliding block is fixedly connected to the lower surface of the movable mounting block (24), and the sliding block is slidably connected inside the arc-shaped mounting groove (35).

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