A fixture for machining an aero-engine blade

Abstract

The utility model relates to clamp technical field especially, relates to a kind of clamp for aero-engine blade processing, including bottom plate and the portal frame being set on bottom plate, fixedly installed with placing table on bottom plate, aero-engine blade is placed on placing table, and two symmetrically arranged placing grooves are opened on placing table, and fixedly installed with hydraulic ram on portal frame.The utility model is pushed down by hydraulic ram and moves frame, limit clamping plate is placed in placing groove, the rotation of cooperation bidirectional screw rod is adjusted, the distance between two limit clamping plates is adjusted, aero-engine blade is lifted, avoid the quality of aero-engine blade when being clamped to aero-engine blade and produce deformation influence, cooperation electric telescopic rod promotes sliding plate to move towards the direction of limit block, the distance between four limit blocks is adjusted, aero-engine blade is pushed to the center position of placing table, prevent limit clamping plate from lifting aero-engine blade, aero-engine blade falls due to unstable gravity center when aero-engine blade is lifted.

Description

Technical Field

[0001] This utility model relates to the field of fixture technology, and in particular to a fixture for machining aero-engine blades. Background Technology

[0002] Aero-engine blades are one of the most core and critical components of an aero-engine, directly determining the engine's efficiency, thrust, lifespan, and reliability.

[0003] After the aero-engine blades are processed and assembled, they are usually clamped onto a transport vehicle by a clamping mechanism. The transport vehicle then transports the aero-engine blades to a designated location for assembly onto the aircraft. However, existing clamping mechanisms typically use two clamping rods to hold the sidewalls of the aero-engine blades. The friction generated by the two clamping rods pressing against the outer wall of the aero-engine blades secures them to the transport vehicle. However, when the two clamping rods clamp the aero-engine blades, they are prone to compressing and deforming the blades, affecting their safe use. Utility Model Content

[0004] The purpose of this invention is to solve the problem that clamping rods in the prior art easily cause deformation of aero-engine blades by compression, and to propose a jig for processing aero-engine blades.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A jig for processing aero-engine blades includes a base plate and a gantry frame mounted on the base plate. A placement platform is fixedly installed on the base plate, and the aero-engine blade is placed on the placement platform. Two symmetrically arranged placement slots are provided on the placement platform. A hydraulic rod is fixedly installed on the gantry frame, and a movable frame is fixedly installed at the output end of the hydraulic rod. Two limiting clamps that lift the aero-engine blade are slidably arranged in the movable frame. The placement platform has two symmetrically arranged sliding cavities. Two symmetrically arranged guide rods are fixedly installed in each of the two sliding cavities, and a sliding plate is slidably arranged on both guide rods. Two opposing sliding grooves are formed on each of the two sliding plates. The placement platform is also provided with two pairs of symmetrically arranged sliding holes, and the two sliding holes are respectively connected to two sliding cavities. Limiting blocks are slidably arranged in both pairs of sliding holes, and the bottom end of the limiting blocks extends into the sliding cavity. The limiting clamp consists of an arc-shaped plate and a support plate, with the support plate fixedly installed at the bottom end of the arc-shaped plate.

[0006] Preferably, a sliding rod is fixedly installed on the limiting block, and the sliding rod is slidably disposed in the sliding groove.

[0007] Preferably, an electric telescopic rod is fixedly installed in each of the two sliding cavities, the end of the electric telescopic rod is fixedly connected to the sliding plate, and a controller for controlling the synchronous extension and retraction of the two electric telescopic rods is fixedly installed on the side wall of the gantry.

[0008] Preferably, two symmetrically arranged slide rails are fixedly installed on the base plate relative to both sides of the placement platform, and the gantry frame is slidably mounted on the two slide rails.

[0009] Preferably, a bidirectional lead screw is rotatably mounted inside the movable frame, and the two ends of the bidirectional lead screw are connected by threads and two sliding blocks. A servo motor for driving the bidirectional lead screw to rotate is fixedly mounted on the side wall of the movable frame.

[0010] Compared with the prior art, the present invention has the following advantages: 1. This utility model uses a hydraulic rod to push the moving frame down, placing the limiting clamping plate in the placement groove. With the rotation of the bidirectional screw, the distance between the two limiting clamping plates is adjusted to lift the aero-engine blade, avoiding deformation during clamping that could affect the quality of the aero-engine blade.

[0011] 2. This utility model uses an electric telescopic rod to push the sliding plate towards the limiting block, adjusts the distance between the four limiting blocks, and pushes the aero-engine blade to the center position of the placement platform to prevent the aero-engine blade from falling due to instability when the limiting clamp lifts it. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the structure of a jig for machining aero-engine blades proposed in this utility model; Figure 2 This is a schematic diagram showing the connection between the hydraulic rod and the moving frame; Figure 3 This is a schematic diagram of the sliding rod and the limiting block structure.

[0013] In the diagram: 1. Base plate; 2. Placement platform; 3. Slide rail; 4. Gantry frame; 5. Hydraulic rod; 6. Moving frame; 7. Two-way lead screw; 8. Sliding block; 9. Servo motor; 10. Limiting clamp; 11. Controller; 12. Placement slot; 13. Sliding cavity; 14. Guide rod; 15. Sliding plate; 16. Sliding groove; 17. Limiting block; 18. Sliding hole; 19. Sliding rod; 20. Electric telescopic rod. Detailed Implementation

[0014] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0015] Reference Figures 1-3 A jig for machining aero-engine blades includes a base plate 1 and a gantry frame 4 mounted on the base plate 1. A placement table 2 is fixedly mounted on the base plate 1. The aero-engine blades are placed on the placement table 2, and two symmetrically arranged placement slots 12 are provided on the placement table 2. A hydraulic rod 5 is fixedly mounted on the gantry frame 4, and a movable frame 6 is fixedly mounted on the output end of the hydraulic rod 5. A bidirectional lead screw 7 is rotatably mounted inside the movable frame 6. The two ends of the bidirectional lead screw 7 are connected by threads and two sliding blocks 8. A servo motor 9 for driving the bidirectional lead screw 7 to rotate is fixedly mounted on the side wall of the movable frame 6. Two limiting clamps 10 for lifting the aero-engine blades are slidably arranged inside the movable frame 6.

[0016] The placement platform 2 has two symmetrically arranged sliding cavities 13. Two symmetrically arranged guide rods 14 are fixedly installed in each of the two sliding cavities 13. A sliding plate 15 is slidably arranged on both guide rods 14. Two oppositely arranged sliding grooves 16 are opened on each of the two sliding plates 15. The placement platform 2 also has two pairs of symmetrically arranged sliding holes 18, and the two sliding holes 18 are respectively connected to the two sliding cavities 13. A limit block 17 is slidably arranged in each of the two pairs of sliding holes 18, and the bottom end of the limit block 17 extends into the sliding cavity 13.

[0017] A sliding rod 19 is fixedly installed on the limiting block 17. The sliding rod 19 is slidably disposed in the sliding groove 16. When the sliding plate 15 pushes the sliding rod 19 to move along the placement groove 12, the distance between the four sliding rods 19 is reduced to prevent it from affecting the movement of the sliding rod 19.

[0018] Electric telescopic rods 20 are fixedly installed in both sliding cavities 13. The ends of the electric telescopic rods 20 are fixedly connected to the sliding plate 15. A controller 11 for controlling the synchronous extension and retraction of the two electric telescopic rods 20 is fixedly installed on the side wall of the gantry frame 4.

[0019] Two symmetrically arranged slide rails 3 are fixedly installed on the base plate 1 on both sides of the placement platform 2, and the gantry frame 4 is slidably set on the two slide rails 3.

[0020] The limiting clamp 10 consists of an arc-shaped plate and a support plate, with the support plate fixedly installed at the bottom of the arc-shaped plate. The support plate lifts the aero-engine blade and centers it through four limiting blocks 17. After centering, the two ends of the aero-engine blade are placed on the upper part of the two placement slots 12. The limiting clamp 10 placed in the placement slots 12 lifts the aero-engine blade from bottom to top.

[0021] It should be noted that the specific model and specifications of the controller 11 need to be selected and determined according to the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be elaborated here.

[0022] The functional principle of this utility model can be explained through the following operation methods: In use, the two electric telescopic rods 20 are extended and retracted by the electrical signal sent by the controller 11, which pushes the two sliding plates 15 to move towards the limiting block 17. The sliding hole 18 limits the movement direction of the limiting block 17, so that the sliding plate 15 pushes the four limiting blocks 17 to move towards each other through the sliding rod 19, and pushes the aero-engine blade to the center position of the placement platform 2. By extending and retracting the hydraulic rod 5, the moving frame 6 moves down and places the bottom end of the limiting clamp 10 into the placement slot 12. The servo motor 9 is turned on to drive the bidirectional lead screw 7 to rotate, so that the two limiting clamps 10 move towards each other and come into contact with the sides of the aero-engine blade. By extending and retracting the hydraulic rod 5 in the opposite direction, the aero-engine blade is lifted up and, together with the gantry 4, slides on the slide rail 3 to transport the aero-engine blade to the transport vehicle.

[0023] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A jig for machining aero-engine blades, comprising a base plate (1) and a gantry (4) mounted on the base plate (1), characterized in that, A placement platform (2) is fixedly installed on the base plate (1). The aero-engine blade is placed on the placement platform (2), and two symmetrically arranged placement slots (12) are opened on the placement platform (2). A hydraulic rod (5) is fixedly installed on the gantry (4), and a movable frame (6) is fixedly installed at the output end of the hydraulic rod (5). Two limiting clamps (10) that lift the aero-engine blade are slidably arranged inside the movable frame (6). The placement platform (2) has two symmetrically arranged sliding cavities (13), and two symmetrically arranged guide rods (14) are fixedly installed in each of the two sliding cavities (13). A sliding plate (15) is slidably arranged on the two guide rods (14), and two oppositely arranged sliding grooves (16) are opened on each of the two sliding plates (15). The placement platform (2) is also provided with two pairs of symmetrically arranged sliding holes (18), and the two sliding holes (18) are respectively connected to two sliding cavities (13). Limiting blocks (17) are slidably arranged in both pairs of sliding holes (18), and the bottom end of the limiting blocks (17) extends into the sliding cavity (13). The limiting clamp (10) consists of an arc-shaped plate and a support plate, with the support plate fixedly installed at the bottom of the arc-shaped plate.

2. The jig for machining aero-engine blades according to claim 1, characterized in that, A sliding rod (19) is fixedly installed on the limiting block (17), and the sliding rod (19) is slidably disposed in the sliding groove (16).

3. The jig for machining aero-engine blades according to claim 2, characterized in that, Electric telescopic rods (20) are fixedly installed in both sliding cavities (13). The ends of the electric telescopic rods (20) are fixedly connected to the sliding plate (15). A controller (11) for controlling the synchronous extension and retraction of the two electric telescopic rods (20) is fixedly installed on the side wall of the gantry frame (4).

4. The jig for machining aero-engine blades according to claim 3, characterized in that, Two symmetrically arranged slide rails (3) are fixedly installed on the base plate (1) relative to the two sides of the placement platform (2), and the gantry frame (4) is slidably arranged on the two slide rails (3).

5. A jig for machining aero-engine blades according to claim 4, characterized in that, A bidirectional lead screw (7) is rotatably installed inside the movable frame (6). The two ends of the bidirectional lead screw (7) are connected by threads and two sliding blocks (8). A servo motor (9) that drives the bidirectional lead screw (7) to rotate is fixedly installed on the side wall of the movable frame (6).

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