An aeroengine blade clamp

Abstract

The application discloses an aero-engine blade clamp, which comprises a clamping table, hydraulic cylinders are fixedly installed on both sides of the inner cavity of the clamping table, moving plates are fixedly installed at the output ends of the hydraulic cylinders, clamping pressing blocks are arranged at the upper ends of the sides of the two moving plates, fixed plates are placed at the two ends of the top of the outer surface of the clamping table, and first bolts are inserted into the two ends of the bottom of the fixed plates. Through the arrangement of the fixed plates, side baffles, first bolts, limiting plates and second bolts, auxiliary support and limiting structures around the blade root of the aero-engine blade can be formed on the top of the clamping table, the inclination, deviation or sliding of the blade during clamping can be effectively prevented, manual support of personnel is not needed, through the arrangement of the hydraulic cylinders, the moving plates and the clamping pressing blocks, the clamping and fixing of the blade can be realized, and deviation of the blade during subsequent quality inspection can be avoided.

Description

Technical Field

[0001] This invention relates to the field of clamping technology, specifically to an aero-engine blade clamp. Background Technology

[0002] As a core precision component of aero-engines, the quality of aero-engine blade production and processing directly determines the engine's operating performance and safety factor. Quality inspection during the production and processing period is particularly critical, as the accuracy of inspection directly affects the pass rate of finished blades and the overall quality of the engine. In the process of blade quality inspection, special fixtures are often used to clamp and fix the blades, providing a stable clamping benchmark for the inspection operation. This is the basic tooling to ensure accurate inspection operations, reliable data, and the orderly conduct of blade quality inspection.

[0003] However, existing aero-engine blade clamps often require manual support during clamping operations due to the lack of corresponding auxiliary support structures. This is necessary to prevent the blades from shifting or slipping. This clamping method is not only cumbersome and time-consuming, significantly reducing the overall efficiency of blade clamping and inspection, but also prone to causing blade bumps and scratches due to human error, damaging precision components and adversely affecting the quality inspection of aero-engine blades. Summary of the Invention

[0004] The purpose of this invention is to provide an aero-engine blade clamp with an auxiliary support structure, which can provide auxiliary support for the blade during blade clamping operations, prevent the blade from shifting, and greatly facilitate the blade clamping operation for personnel.

[0005] To achieve the above objectives, the present invention provides the following technical solution: an aero-engine blade clamp, comprising a clamping platform, wherein hydraulic cylinders are fixedly installed on both sides of the inner cavity of the clamping platform, and movable plates are fixedly installed on the output ends of the hydraulic cylinders. Clamping blocks are provided at the upper ends of the two movable plates on the side closer to each other. Fixed plates are placed at both ends of the top of the outer surface of the clamping platform, and first bolts are inserted at both ends of the bottom of the fixed plates. A limiting plate is threadedly connected between the lower ends of the two first bolts. The top of the limiting plate contacts the top of the inner cavity of the clamping platform. Second bolts are contacted around the perimeter of the two fixed plates on the side away from each other, and side baffles are contacted at both ends of the two fixed plates on the side closer to each other. The surface of the second bolts is threadedly connected to the surface of the side baffles.

[0006] As a preferred embodiment, a locking groove is provided at the middle of the two clamping blocks on the side away from each other, a snap-fit ​​groove is provided at the upper right end of the moving plate, a receiving groove is provided at the upper end of the moving plate, a rotating shaft is movably connected to the left end of the receiving groove through a bearing, a sector-shaped locking disc is fixedly installed at the middle end of the rotating shaft, and the surface of the sector-shaped locking disc is inserted into the surface of the locking groove.

[0007] As a preferred embodiment, a crossbar is fixedly installed on the side of the sector-shaped locking disc, a baffle is fixedly installed on the right side of the crossbar, a grip sleeve is sleeved on the right end of the crossbar, a pressure spring is sleeved between the inner cavity of the grip sleeve and the right end of the crossbar, the right side of the pressure spring contacts the left side of the baffle, and a snap-fit ​​block is fixedly connected to the left end of the outer surface of the grip sleeve, the surface of the snap-fit ​​block is inserted into the surface of the snap-fit ​​groove.

[0008] As a preferred embodiment, a positioning plate is fixedly installed on the upper end of the two movable plates on the side close to each other, and positioning grooves are provided at both ends of the two clamping blocks on the side far from each other. The surface of the positioning groove is slidably connected to the surface of the positioning plate, and the positioning plate and the positioning groove are both T-shaped.

[0009] As a preferred embodiment, both ends of the top of the clamping platform are provided with a first through groove, and the number of the first through grooves is four, with the surface of the first bolt intersecting the surface of the first through groove.

[0010] As a preferred embodiment, both ends of the fixing plate are provided with a second through groove, and the surface of the second bolt is inserted into the surface of the second through groove.

[0011] As a preferred embodiment, a first reinforcing block is fixedly connected to the lower end of the fixing plate, and a second reinforcing block is fixedly connected to the surface of the side baffle.

[0012] As a preferred embodiment, a receiving hole is provided at the middle of the top of the clamping platform, and a guide slide rod is fixedly installed between the two sides of the receiving hole, with the lower end of the moving plate slidably connected to the surface of the guide slide rod.

[0013] As a preferred embodiment, both the fixing plate and the side baffle are L-shaped.

[0014] As a preferred embodiment, mounting plates are fixedly installed on the lower ends of both sides of the outer surface of the clamping table, and mounting holes are provided at both ends of the mounting plates.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention, through the setting of a fixed plate, side baffle, first bolt, limiting plate and second bolt, can form an auxiliary support and limiting structure around the blade root of the aero-engine on the top of the clamping table, effectively preventing the blade from tilting, shifting or slipping during the clamping process, without the need for manual support. At the same time, through the setting of hydraulic cylinder, moving plate and clamping pressure block, the blade can be clamped and fixed, avoiding the blade from shifting during subsequent quality inspection. With the overall cooperation, the convenience and safety of aero-engine blade clamping operation are effectively improved, avoiding blade collision damage caused by human error in supporting.

[0016] 2. This invention, through the setting of positioning grooves and positioning plates, can effectively position the clamping block and the moving plate, preventing misalignment or displacement of the clamping block and the moving plate during installation. Furthermore, through the setting of locking grooves and fan-shaped locking discs, it can effectively limit the vertical direction of the clamping block, preventing it from loosening from the surface of the moving plate. Moreover, when personnel need to replace the clamping block later according to the different types of tenon grooves at the blade roots of different specifications of aero-engine blades, personnel can pull the grip sleeve and the locking block to the right. While moving and compressing the pressure spring, until the locking block can disengage from the locking groove, the operator can pull the grip sleeve and crossbar to drive the sector locking disc and rotating shaft to rotate axially along the bearing on the receiving groove until the sector locking disc can disengage from the locking groove, thus releasing the vertical limit of the clamping block. Then, the operator can slide the clamping block off from the top of the moving plate, which greatly facilitates the operator to quickly replace the clamping block as needed, improving the convenience and efficiency of the replacement operation.

[0017] 3. The present invention, through the setting of the first through groove, can accommodate and guide the first bolt; through the setting of the second through groove, can accommodate and guide the second bolt; through the setting of the first reinforcing block and the second reinforcing block, the support strength of the fixed plate and the side baffle are respectively improved; through the setting of the receiving hole and the guide slide rod, the purpose of supporting and guiding the moving plate is achieved, so as to avoid the moving plate tilting and deviating during the movement; through the setting of the mounting plate and the mounting hole, it is convenient for personnel to use bolts to install and fix the clamping platform. Attached Figure Description

[0018] Figure 1 This is a perspective view of the present invention; Figure 2 For the present invention Figure 1 Enlarged view of section A in the image; Figure 3 This is a schematic diagram of the structure of the present invention from a bottom view; Figure 4 This is a schematic diagram of the fixing plate structure of the present invention; Figure 5 This is a partial structural diagram of the movable plate of the present invention; Figure 6 This is a top view cross-sectional structural diagram of the movable plate of the present invention; Figure 7 This is a top view cross-sectional structural diagram of the grip sleeve of the present invention.

[0019] In the diagram: 1. Clamping platform; 2. Mounting plate; 3. Moving plate; 4. Clamping block; 5. Fixing plate; 6. First through slot; 7. First bolt; 8. First reinforcing block; 9. Second through slot; 10. Second bolt; 11. Limiting plate; 12. Hydraulic cylinder; 13. Receiving hole; 14. Guide slide rod; 15. Second reinforcing block; 16. Side baffle; 17. Receiving slot; 18. Grip sleeve; 19. Snap-fit ​​block; 20. Snap-fit ​​groove; 21. Positioning groove; 22. Positioning plate; 23. Locking groove; 24. Rotating shaft; 25. Fan-shaped locking disc; 26. Crossbar; 27. Compression spring; 28. Stop plate. 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] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0022] The components in this application, such as clamping platform 1, mounting plate 2, moving plate 3, clamping pressure block 4, fixing plate 5, first through groove 6, first bolt 7, first reinforcing block 8, second through groove 9, second bolt 10, limiting plate 11, hydraulic cylinder 12, receiving hole 13, guide slide rod 14, second reinforcing block 15, side baffle 16, receiving groove 17, grip sleeve 18, snap-fit ​​block 19, snap-fit ​​groove 20, positioning groove 21, positioning plate 22, locking groove 23, rotating shaft 24, sector locking disc 25, crossbar 26, pressure spring 27, and baffle 28, are all general standard parts or parts known to those skilled in the art. Their structure and principle are common knowledge and can be learned by those skilled in the art through technical manuals or conventional experimental methods.

[0023] Example 1: Please see Figures 1-6As shown, the present invention provides an aero-engine blade clamp, including a clamping platform 1. Hydraulic cylinders 12 are fixedly installed on both sides of the inner cavity of the clamping platform 1. Movable plates 3 are fixedly installed on the output ends of the hydraulic cylinders 12. Clamping blocks 4 are provided on the upper ends of the two movable plates 3 that are close to each other. Fixed plates 5 are placed on both ends of the top of the outer surface of the clamping platform 1. First bolts 7 are inserted through both ends of the bottom of the fixed plates 5. Limiting plates 11 are threadedly connected between the lower ends of the two first bolts 7. The top of the limiting plates 11 contacts the top of the inner cavity of the clamping platform 1. Second bolts 10 are contacted on all four sides of the two fixed plates 5 that are far apart from each other. Side baffles 16 are contacted on both ends of the two fixed plates 5 that are close to each other. The surface of the second bolts 10 is threadedly connected to the surface of the side baffles 16.

[0024] In this technical solution, during the clamping operation of aero-engine blades, personnel can place the blade root between the fixed plate 5 and the side baffle 16. During this process, the fixed plate 5 and the side baffle 16 can provide support and limit the blade root around its perimeter, preventing the blade from tilting or shifting during subsequent clamping operations. Subsequently, personnel can extend the hydraulic cylinder 12 to push the moving plate 3 and the clamping block 4 to move, causing the tenon groove on the surface of the clamping block 4 to apply pressure to both sides of the blade root under the action of movement, thereby completing the blade clamping operation. During the use of this fixture, personnel can use an Allen wrench to loosen the first bolt 7 between the limiting plate 11 and the second bolt 10 between the side baffle 16. After that, personnel can move and adjust the two sets of fixed plates 5 on the clamping table 1 and the two sets of side baffles 16 on the fixed plate 5, effectively improving the applicability of the fixed plate 5 and the side baffle 16 in providing auxiliary support for the blade root during the mass production of aero-engine blades.

[0025] It should be noted that the hydraulic cylinder 12 uses the industry-standard telescopic hydraulic drive component. The two sets of hydraulic cylinders 12 are equipped with the same set of hydraulic control valves and hydraulic power pumps. The extension stroke and action rate of the two sets of hydraulic cylinders 12 are synchronously controlled by the hydraulic control valves.

[0026] Example 2: Based on Embodiment 1, the present invention is as follows: Figures 5-7As shown, two clamping blocks 4 are provided with locking grooves 23 at their midpoints on opposite sides. A snap-fit ​​groove 20 is provided at the upper right end of the moving plate 3, and a receiving groove 17 is provided at the upper end of the moving plate 3. A rotating shaft 24 is movably connected to the left end of the receiving groove 17 via a bearing. A sector-shaped locking disc 25 is fixedly installed at the midpoint of the rotating shaft 24. The surface of the sector-shaped locking disc 25 is inserted into the surface of the locking groove 23. A crossbar 26 is fixedly installed on the side of the sector-shaped locking disc 25. A stop plate 28 is fixedly installed on the right side of the crossbar 26, and a gripping sleeve 18 is fitted onto the right end of the crossbar 26. A pressure spring 27 is fitted between the inner cavity of the grip sleeve 18 and the right end of the crossbar 26. The right side of the pressure spring 27 contacts the left side of the baffle 28. A snap-fit ​​block 19 is fixedly connected to the left end of the outer surface of the grip sleeve 18. The surface of the snap-fit ​​block 19 is inserted into the surface of the snap-fit ​​groove 20. A positioning plate 22 is fixedly installed on the upper end of the two moving plates 3 that are close to each other. Positioning grooves 21 are provided at both ends of the two clamping blocks 4 that are far away from each other. The surface of the positioning groove 21 is slidably connected to the surface of the positioning plate 22. The positioning plate 22 and the positioning groove 21 are both T-shaped.

[0027] In this technical solution, the positioning groove 21 and positioning plate 22 effectively position the clamping block 4 and the moving plate 3, preventing misalignment or displacement of the clamping block 4 and the moving plate 3 during installation. The locking groove 23 and fan-shaped locking disc 25 effectively limit the vertical movement of the clamping block 4, preventing it from detaching from the surface of the moving plate 3. Furthermore, when personnel need to replace the clamping block 4 later according to different types of blade root tenons for aero-engines, they can pull the grip sleeve 18 and the locking block 19 to the right to move it. While the spring 27 is compressed, the locking block 19 is disengaged from the locking groove 20. Then, the operator can pull the grip sleeve 18 and the crossbar 26 to drive the sector locking disc 25 and the rotating shaft 24 to rotate axially along the bearing on the receiving groove 17 until the sector locking disc 25 is disengaged from the locking groove 23. This releases the vertical limit of the clamping block 4, allowing the operator to slide the clamping block 4 off from the top of the moving plate 3. This greatly facilitates the operator to quickly replace the clamping block 4 as needed, improving the convenience and efficiency of the replacement operation.

[0028] Example 3: Based on Embodiment 1, the present invention is as follows: Figures 1-4As shown, the clamping platform 1 has four first through slots 6 at both ends of its top. The surface of the first bolt 7 passes through the surface of the first through slot 6. The fixing plate 5 has two second through slots 9 at both ends of its top. The surface of the second bolt 10 passes through the surface of the second through slot 9. The lower end of the fixing plate 5 is fixedly connected to a first reinforcing block 8. The surface of the side baffle 16 is fixedly connected to a second reinforcing block 15. The middle of the top of the clamping platform 1 has a receiving hole 13. A guide slide rod 14 is fixedly installed between the two sides of the receiving hole 13. The lower end of the moving plate 3 is slidably connected to the surface of the guide slide rod 14. The fixing plate 5 and the side baffle 16 are both L-shaped. The lower ends of both sides of the outer surface of the clamping platform 1 are fixedly installed with mounting plates 2. The mounting plates 2 have mounting holes at both ends.

[0029] In this technical solution, the first through groove 6 can accommodate and guide the first bolt 7, and the second through groove 9 can accommodate and guide the second bolt 10. The first reinforcing block 8 and the second reinforcing block 15 respectively enhance the support strength of the fixed plate 5 and the side baffle 16. The accommodating hole 13 and the guide slide rod 14 achieve the purpose of supporting and guiding the moving plate 3, preventing the moving plate 3 from tilting and shifting during movement. The mounting plate 2 and the mounting hole facilitate the use of bolts to install and fix the clamping table 1.

[0030] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit the scope of protection of the present invention. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the essence and scope of the technical solutions of the present invention.

Claims

1. An aero-engine blade clamp, comprising a clamping table (1), characterized in that: Hydraulic cylinders (12) are fixedly installed on both sides of the inner cavity of the clamping table (1). A movable plate (3) is fixedly installed at the output end of the hydraulic cylinder (12). A clamping block (4) is provided at the upper end of the two movable plates (3) on the side close to each other. Fixed plates (5) are placed at both ends of the top of the outer surface of the clamping table (1). First bolts (7) are inserted at both ends of the bottom of the fixed plates (5). A limiting plate (11) is threaded between the lower ends of the two first bolts (7). The top of the limiting plate (11) contacts the top of the inner cavity of the clamping table (1). Second bolts (10) are contacted around the sides of the two fixed plates (5) on the side away from each other. Side baffles (16) are contacted at both ends of the two fixed plates (5) on the side close to each other. The surface of the second bolt (10) is threadedly connected to the surface of the side baffle (16).

2. An aeroengine blade clamp according to claim 1, wherein: The two clamping blocks (4) are provided with locking grooves (23) at the middle of the side away from each other. The upper right end of the moving plate (3) is provided with a snap-fit ​​groove (20). The upper end of the moving plate (3) is provided with a receiving groove (17). The left end of the receiving groove (17) is movably connected to a rotating shaft (24) through a bearing. The middle end of the rotating shaft (24) is fixedly installed with a fan-shaped locking disc (25). The surface of the fan-shaped locking disc (25) is inserted into the surface of the locking groove (23).

3. The aero-engine blade clamp according to claim 2, characterized in that: A crossbar (26) is fixedly installed on the side of the sector-shaped locking disc (25). A baffle (28) is fixedly installed on the right side of the crossbar (26). A grip sleeve (18) is sleeved on the right end of the crossbar (26). A pressure spring (27) is sleeved between the inner cavity of the grip sleeve (18) and the right end of the crossbar (26). The right side of the pressure spring (27) contacts the left side of the baffle (28). A snap-fit ​​block (19) is fixedly connected to the left end of the outer surface of the grip sleeve (18). The surface of the snap-fit ​​block (19) is inserted into the surface of the snap-fit ​​groove (20).

4. The aero-engine blade clamp according to claim 1, characterized in that: Positioning plates (22) are fixedly installed on the upper ends of the two movable plates (3) on the side close to each other, and positioning grooves (21) are provided at both ends of the two clamping blocks (4) on the side far from each other. The surface of the positioning groove (21) is slidably connected to the surface of the positioning plate (22). The positioning plate (22) and the positioning groove (21) are both T-shaped.

5. The aero-engine blade clamp according to claim 1, characterized in that: The clamping platform (1) has four first through slots (6) at both ends of its top. The surface of the first bolt (7) is inserted into the surface of the first through slot (6).

6. The aero-engine blade clamp according to claim 1, characterized in that: The fixing plate (5) has a second through groove (9) at both ends, and the surface of the second bolt (10) is inserted into the surface of the second through groove (9).

7. The aero-engine blade clamp according to claim 1, characterized in that: The lower end of the fixed plate (5) is fixedly connected to a first reinforcing block (8), and the surface of the side baffle (16) is fixedly connected to a second reinforcing block (15).

8. The aero-engine blade clamp according to claim 1, characterized in that: The clamping platform (1) has a receiving hole (13) at the middle of its top. A guide slide rod (14) is fixedly installed between the two sides of the receiving hole (13). The lower end of the moving plate (3) is slidably connected to the surface of the guide slide rod (14).

9. The aero-engine blade clamp according to claim 1, characterized in that: Both the fixing plate (5) and the side baffle (16) are L-shaped.

10. The aero-engine blade clamp according to claim 1, characterized in that: Mounting plates (2) are fixedly installed on the lower ends of both sides of the outer surface of the mounting table (1), and mounting holes are provided at both ends of the mounting plates (2).

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