Aero-engine blade polishing clamp

Abstract

The utility model relates to the technical field of aero-engine blade machining, and discloses an aero-engine blade polishing clamp which comprises a workbench, a gear barrel is movably connected in the workbench, a clamp is arranged at the top of the gear barrel, an annular elastic piece is arranged in the clamp, and the annular elastic piece is connected with the gear barrel. The surface of the annular elastic piece is fixedly connected with an extrusion rod, the side, away from the extrusion rod, of the annular elastic piece is fixedly connected to the interior of a clamp, the right side of the clamp is fixedly connected with a pushing toothed plate, the surface of the pushing toothed plate is meshed with a first gear, and the inner side of the first gear is meshed with a fixed toothed plate. According to the fixing device for the tenon roots of the aero-engine blades, through mutual cooperation of the first gear motor, the eccentric wheel, the first gear, the pushing toothed plate and other structures, the extrusion rods on the inner sides of the clamps are driven to extrude and fix the aero-engine blades, and the effect of fixing the tenon roots of the aero-engine blades of different shapes is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft engine blade processing, in particular to an aircraft engine blade polishing fixture. Background Art

[0002] As an important part of aircraft engines, the geometric accuracy, surface quality and quality consistency of blades will directly affect important indicators such as the working efficiency, safety and service life of the equipment. There are many blades on aircraft engines, and they require high precision and need to be processed through multiple processes. Therefore, the stability and convenience of clamping installation are very important.

[0003] When polishing an aircraft engine blade, a fixture is required for fixing. After searching, Chinese patent announcement number: CN219685074U discloses an aircraft engine blade polishing fixture, which is used to clamp the aircraft engine blade to be polished with high stability and high precision. The fixture includes a clamp body, an end face positioning block, a rotating pressure plate, a slider, an inclined wedge shaft and an adjusting nut; the aircraft engine blade is slid into the clamp body from the front end of the clamp body along the edge plate groove and the tenon root groove. After assembly, the vertical axis of the clamp body coincides with the blade stacking axis of the aircraft engine blade; the end face positioning block is fixedly connected to the rear end face of the clamp body, completely covering the rear end faces of the edge plate and the tenon root; the rotating pressure plate is rotatably arranged on the front end face of the clamp body with the inclined wedge shaft as the rotating axis, completely covering the front end faces of the edge plate and the tenon root; when the inclined wedge shaft gradually moves forward along the longitudinal axis direction of the clamp body, the wedge surface gradually contacts with the inclined top wall until it completely coincides, so that the top end face of the slider contacts with the bottom face of the tenon root of the aircraft engine blade and presses the aircraft engine blade tightly.

[0004] The above-mentioned prior art solution has the following defects. In the above-mentioned technical solution, the clamp can only fix the tenon of a blade of one shape. When processing tenons of different shapes, the clamp needs to be replaced, which wastes a lot of time. In addition, after polishing one side, the aircraft engine blade needs to be removed and turned over to the unpolished side for fixation again, which increases the polishing time of the aircraft engine blade and is inefficient. Therefore, an aircraft engine blade polishing clamp is proposed to solve the above problems. Utility Model Content

[0005] In order to make up for the above shortcomings, the utility model provides an aircraft engine blade polishing fixture, aiming to improve the problem that the prior art cannot adapt to different aircraft engine blade tenons.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] A polishing fixture for aircraft engine blades comprises a workbench, the workbench is movably connected with a gear barrel inside, a fixture is arranged on the top of the gear barrel, an annular spring sheet is arranged inside the fixture, a squeezing rod is fixedly connected to the surface of the annular spring sheet, a side of the annular spring sheet away from the squeezing rod is fixedly connected to the inside of the fixture, a pushing tooth plate is fixedly connected to the right side of the fixture, a first gear is meshed on the surface of the pushing tooth plate, a fixed tooth plate is meshed on the inner side of the first gear, a side of the fixed tooth plate away from the first gear is fixedly installed on the top of the gear barrel, a moving block is movably connected to the top of the first gear, an eccentric wheel is movably connected to the inside of the moving block, a first reduction motor is fixedly installed inside the gear barrel 2, an output end of the first reduction motor passes through the surface of the gear barrel and is fixedly connected to the inside of the eccentric wheel, a rotating component is arranged at the bottom of the gear barrel, and a protective component is arranged on the top of the workbench;

[0008] As a further description of the above technical solution:

[0009] The rotating assembly includes a second reduction motor, the second reduction motor is fixedly connected to the bottom of the workbench, the output end of the second reduction motor passes through the inside of the workbench and is fixedly connected to the inside of the second gear, and the second gear is meshed with the gear barrel;

[0010] As a further description of the above technical solution:

[0011] The protection assembly includes a protection box, and the protection box is fixedly installed on the top of the workbench;

[0012] As a further description of the above technical solution:

[0013] A rubber frame is fixedly installed on one side of the protection box close to the clamp, and the surface of the rubber frame is in contact with the pushing tooth plate;

[0014] As a further description of the above technical solution:

[0015] A sealing ring is fixedly mounted on the surface of the gear barrel, and a side of the sealing ring away from the gear barrel is in contact with the workbench;

[0016] As a further description of the above technical solution:

[0017] A silicone pad is fixedly installed on the inner side of the extrusion rod;

[0018] As a further description of the above technical solution:

[0019] The bottom of the second reduction motor is fixedly connected with a support block, and the top of the support block is fixedly connected to the bottom of the workbench;

[0020] As a further description of the above technical solution:

[0021] A slide groove is provided on the top of the workbench, and a clamp is movably connected inside the slide groove.

[0022] The utility model has the following beneficial effects:

[0023] 1. In the utility model, the first reduction motor, the eccentric wheel, the first gear and the push gear plate cooperate with each other to drive the extrusion rod inside the clamp to extrude and fix the aircraft engine blades, thereby achieving the effect of fixing the tenons of aircraft engine blades of different shapes.

[0024] 2. In the present invention, with the cooperation of the second reduction motor and the second gear structure, the polished aircraft engine blades can be turned over to solve the problem of manually adjusting the unpolished side of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A three-dimensional schematic diagram of an aircraft engine blade polishing fixture proposed by the utility model;

[0026] Figure 2 This is a schematic exploded three-dimensional structure diagram of an eccentric wheel of an aircraft engine blade polishing fixture proposed by the utility model;

[0027] Figure 3 This is a schematic diagram of the cross-sectional three-dimensional structure of a moving block of an aircraft engine blade polishing fixture proposed by the utility model;

[0028] Figure 4 This is a three-dimensional structural schematic diagram of a gear barrel of an aircraft engine blade polishing fixture proposed by the utility model;

[0029] Figure 5 for Figure 2 The enlarged view of point A in the middle;

[0030] Figure 6 This is a schematic diagram of an exploded three-dimensional structure of a support block of an aero-engine blade polishing fixture proposed by the utility model;

[0031] Figure 7 The utility model is a schematic diagram of the three-dimensional structure of the second gear of the aero-engine blade polishing fixture.

[0032] Legend:

[0033] 1. Workbench; 2. Gear barrel; 3. Clamp; 4. Annular spring; 5. Extrusion rod; 6. Pushing gear plate; 7. First gear; 8. Fixed gear plate; 9. Moving block; 10. Eccentric wheel; 11. First reduction motor; 12. Second reduction motor; 13. Second gear; 14. Protection box; 15. Rubber frame; 16. Sealing ring; 17. Silicone pad; 18. Support block; 19. Slide groove. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0035] Reference Figure 1-3 The utility model provides an embodiment: an aircraft engine blade polishing fixture, comprising a workbench 1, a slide groove 19 is provided on the top of the workbench 1, a fixture 3 is movably connected inside the slide groove 19, the fixture 3 is guided and limited by the slide groove 19, a gear barrel 2 is movably connected inside the workbench 1, the aircraft engine blade is turned over by rotating the gear barrel 2, a sealing ring 16 is fixedly installed on the surface of the gear barrel 2, the side of the sealing ring 16 away from the gear barrel 2 is in contact with the workbench 1, and the sealing ring 16 is installed to prevent the debris generated by polishing from falling into the gap at the connection between the gear barrel 2 and the workbench 1, a fixture 3 is provided on the top of the gear barrel 2, an annular spring sheet 4 is provided inside the fixture 3, an extrusion rod 5 is fixedly connected to the surface of the annular spring sheet 4, a silicone pad 17 is fixedly installed on the inner side of the extrusion rod 5, and the silicone pad 17 is installed to prevent the extrusion rod 5 from squeezing the aircraft engine blade. Its deformation, the side of the annular spring piece 4 away from the extrusion rod 5 is fixedly connected to the inside of the clamp 3, the right side of the clamp 3 is fixedly connected with a pushing tooth plate 6, the surface of the pushing tooth plate 6 is meshed with a first gear 7, the inner side of the first gear 7 is meshed with a fixed tooth plate 8, the side of the fixed tooth plate 8 away from the first gear 7 is fixedly installed on the top of the gear barrel 2, the top of the first gear 7 is movably connected with a moving block 9, the inside of the moving block 9 is movably connected with an eccentric wheel 10, the inside of the gear barrel 2 is fixedly installed with a first reduction motor 11, the output end of the first reduction motor 11 passes through the surface of the gear barrel 2 and is fixedly connected to the inside of the eccentric wheel 10, by starting the first reduction motor 11, the eccentric wheel 10 is driven to rotate, the eccentric wheel 10 drives the moving block 9 to deviate, and at the same time the moving block 9 drives the first gear 7 to move along the fixed tooth plate 8 toward the clamp 3, and drives the pushing tooth plate 6 to push the clamp 3 to extrude and fix the aircraft engine blade.

[0036] Reference Figure 4-6A rotating assembly is provided at the bottom of the gear barrel 2, and the rotating assembly includes a second reduction motor 12, and the second reduction motor 12 is fixedly connected to the bottom of the workbench 1, and the output end of the second reduction motor 12 passes through the interior of the workbench 1 and is fixedly connected to the interior of the second gear 13, and the second gear 13 is meshed with the gear barrel 2. The second gear 13 is driven to rotate by starting the second reduction motor 12, and at the same time, the second gear 13 drives the gear barrel 2 meshed on the surface to rotate, and the bottom of the second reduction motor 12 is fixedly connected to a support block 18, and the top of the support block 18 is fixedly connected to the bottom of the workbench 1, and the second reduction motor 12 is supported and protected by installing the support block 18.

[0037] Reference Figure 5-7 A protection component is provided on the top of the workbench 1, and the protection component includes a protection box 14, which is fixedly installed on the top of the workbench 1. The protection box 14 is installed to prevent debris generated during grinding from falling onto the meshing portion between the first gear 7 and the pushing tooth plate 6, causing the movement process to jam. A rubber frame 15 is fixedly installed on one side of the protection box 14 close to the clamp 3, and the surface of the rubber frame 15 is in contact with the pushing tooth plate 6. The rubber frame 15 is installed to prevent debris from entering the protection box 14 along with the pushing tooth plate 6.

[0038] Working principle: When the staff polishes the aircraft engine blades, they first start the first reduction motor 11 to drive the eccentric wheel 10 to rotate, and the eccentric wheel 10 drives the moving block 9 to shift. At the same time, the moving block 9 drives the first gear 7 to move along the fixed tooth plate 8 toward the clamp 3, and drives the pushing tooth plate 6 to push the clamp 3 to squeeze and fix the aircraft engine blades. When the extrusion rod 5 on the surface of the clamp 3 touches the aircraft blade, the extrusion rod 5 moves toward the inside of the clamp 3, squeezing the annular spring sheet 4 to make it elastically compressed. At the same time, the annular spring sheet 4 elastically extends, driving the extrusion rod 5 to squeeze and fix the aircraft blade. When one side is polished, the second reduction motor 12 is started to drive the second gear 13 to rotate. At the same time, the second gear 13 drives the gear barrel 2 engaged on the surface to rotate.

[0039] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine blade polishing fixture, comprising a workbench (1), characterized in that: The workbench (1) is movably connected to a gear barrel (2) inside, a clamp (3) is arranged on the top of the gear barrel (2), an annular spring sheet (4) is arranged inside the clamp (3), a squeeze rod (5) is fixedly connected to the surface of the annular spring sheet (4), a side of the annular spring sheet (4) away from the squeeze rod (5) is fixedly connected to the inside of the clamp (3), a pushing tooth plate (6) is fixedly connected to the right side of the clamp (3), a first gear (7) is meshed on the surface of the pushing tooth plate (6), and a fixed tooth plate (8) is meshed on the inner side of the first gear (7). The fixed tooth plate (8) is fixedly mounted on the top of the gear barrel (2) at a side away from the first gear (7); the top of the first gear (7) is movably connected to a moving block (9); the interior of the moving block (9) is movably connected to an eccentric wheel (10); a first reduction motor (11) is fixedly mounted inside the gear barrel (2); the output end of the first reduction motor (11) passes through the surface of the gear barrel (2) and is fixedly connected to the interior of the eccentric wheel (10); a rotating component is arranged at the bottom of the gear barrel (2); and a protective component is arranged at the top of the workbench (1).

2. The aerospace engine blade polishing fixture according to claim 1, characterized in that: The rotating assembly comprises a second reduction motor (12), the second reduction motor (12) is fixedly connected to the bottom of the workbench (1), the output end of the second reduction motor (12) passes through the interior of the workbench (1) and is fixedly connected to the interior of a second gear (13), and the second gear (13) is meshed with the gear barrel (2).

3. The aerospace engine blade polishing fixture according to claim 1, characterized in that: The protection assembly comprises a protection box (14), and the protection box (14) is fixedly mounted on the top of the workbench (1).

4. The aerospace engine blade polishing fixture according to claim 3, characterized in that: A rubber frame (15) is fixedly mounted on one side of the protection box (14) close to the clamp (3), and the surface of the rubber frame (15) is in contact with the pushing tooth plate (6).

5. The aerospace engine blade polishing fixture according to claim 1, characterized in that: A sealing ring (16) is fixedly mounted on the surface of the gear barrel (2), and the side of the sealing ring (16) away from the gear barrel (2) is in contact with the workbench (1).

6. The aerospace engine blade polishing fixture according to claim 1, characterized in that: A silicone pad (17) is fixedly mounted on the inner side of the extrusion rod (5).

7. The aerospace engine blade polishing fixture according to claim 2, characterized in that: The bottom of the second reduction motor (12) is fixedly connected to a support block (18), and the top of the support block (18) is fixedly connected to the bottom of the workbench (1).

8. The aerospace engine blade polishing fixture according to claim 1, characterized in that: A slide groove (19) is provided on the top of the workbench (1), and a clamp (3) is movably connected inside the slide groove (19).

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