Fixing device for aircraft engine blade machining

Abstract

The utility model relates to the technical field of aircraft engine blade machining, and discloses a fixing device for aircraft engine blade machining, which comprises a base, the top of the base is fixedly connected with a supporting plate, and the top of the supporting plate is provided with a clamping mechanism. The bottom of the limiting strip can be supported, the limiting strip can limit the initial placement position of the blade body, the telescopic rod is connected with the vertical plate and the auxiliary plate, shaking of the blade body when the blade body is placed in the limiting strip can be reduced, the hydraulic cylinder is used for driving the second clamping plate to move, and clamping and fixing of the blade body can be achieved through the first positioning plate and the second positioning plate; the contact area of an auxiliary plate, a first positioning plate and a second positioning plate with the blade body is large, shaking of the blade body during machining can be reduced, the inclination angle of an L-shaped frame can be adjusted through rotation of a second bevel gear and a first bevel gear, and therefore the use direction of the blade body and the use direction of a hydraulic cylinder are changed.

Description

Technical Field

[0001] The utility model application relates to the technical field of aircraft engine blade processing, in particular to a fixing device for aircraft engine blade processing. Background Art

[0002] When using the above technology, it was found that the following technical problems exist in the existing technology: aircraft engine blades are key components in aircraft engines and play a vital role in the performance and reliability of the aircraft.

[0003] When using the above technology, it was found that the following technical problems exist in the existing technology: In the existing technology, during the processing of aircraft engine blades, the blades need to be clamped and fixed. The contact area between the clamping structure and the blades is small, and it is easy to shake during clamping, thereby reducing the stability of the blades during processing. For this reason, we designed a fixing device for processing aircraft engine blades to provide another technical solution to the above technical problems. Utility Model Content

[0004] In order to solve the problem that the contact area between the clamping structure and the blade is small, shaking is easy to occur during clamping, thereby reducing the stability of the blade during processing, the utility model provides a fixing device for aircraft engine blade processing to solve the above problem.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] A fixing device for processing aircraft engine blades includes a base, the top of the base is fixedly connected to a support plate, the top of the support plate is provided with a clamping mechanism, the clamping mechanism includes a first clamping plate, a hydraulic cylinder and a vertical plate, one side of the first clamping plate is fixedly connected to a second positioning plate, the top of the second positioning plate is fixedly connected to the vertical plate, one side of the vertical plate is fixedly connected to a telescopic rod, one end of the telescopic rod is fixedly connected to an auxiliary plate, one side of the auxiliary plate is overlapped with a blade body, the bottom of the blade body is engaged with a limiting strip, the bottom of the limiting strip is fixedly connected to a fixing plate, one side of the fixing plate is fixedly connected to the first clamping plate, the other side of the blade body is overlapped with the first positioning plate, one side of the first positioning plate is fixedly connected to the second clamping plate, and one side of the second clamping plate is fixedly connected to the hydraulic cylinder.

[0007] As a preferred embodiment of the fixing device for processing aircraft engine blades provided by the utility model, the bottom of the hydraulic cylinder is fixedly connected to a connecting plate 1, the bottom of the connecting plate 1 is fixedly connected to an L-shaped frame, and one side of the L-shaped frame is fixedly connected to a connecting plate 2.

[0008] As a preferred embodiment of the fixing device for processing aircraft engine blades provided by the present invention, a connecting piece is fixedly connected to one side of the L-shaped frame, one end of one of the connecting pieces is rotatably connected to a support frame, and the bottom of the support frame is fixedly connected to the support plate.

[0009] As a preferred embodiment of the fixing device for processing aircraft engine blades provided by the present invention, a bevel gear 1 is inserted through the outside of the other connecting member, one side of the bevel gear 1 is engaged with a bevel gear 2, and one side of the bevel gear 2 is fixedly connected to the output shaft of the motor.

[0010] As a preferred embodiment of the fixing device for processing aircraft engine blades provided by the utility model, one side of the motor is fixedly connected to an auxiliary frame, the bottom of the auxiliary frame is fixedly connected to the support plate, and one side of the auxiliary frame is rotatably connected to the second bevel gear.

[0011] As a preferred embodiment of the fixing device for machining aircraft engine blades provided by the present invention, a support bar is fixedly connected to the top of the support plate, and the top of the support bar is overlapped with the L-shaped frame.

[0012] As a preferred embodiment of the fixing device for machining aircraft engine blades provided by the present invention, an extension plate is slidably connected to one side of the base, and a mounting hole is provided on the top of the extension plate.

[0013] At the same time, through the above technical solutions, the present invention has at least the following beneficial effects:

[0014] 1. In the utility model, the bottom of the limit bar can be supported by the fixed connection between the fixed plate and the limit bar, and the limit bar can limit the initial placement position of the blade body. The telescopic rod connects the vertical plate and the auxiliary plate, which can reduce the shaking of the blade body when placed inside the limit bar. The hydraulic cylinder is used to drive the clamping plate 2 to move, and the positioning plate 1 and the positioning plate 2 can be used to clamp and fix the blade body. The contact area between the auxiliary plate, the positioning plate 1 and the positioning plate 2 and the blade body is large, which can reduce the shaking of the blade body during processing.

[0015] 2. In the utility model, the bottom of the support bar is fixedly connected to the support plate, so that the bottom of the support bar can be supported, and the support bar can support the bottom of the L-shaped frame. By rotating the bevel gear 2 and the bevel gear 1, the inclination angle of the L-shaped frame can be adjusted, thereby changing the use direction of the blade body and the hydraulic cylinder. The base can be used to guide the movement of the extension plate, and the contact area between the bottom of the base and the installation position can be increased by the extension plate, thereby improving the stability of the device during use and avoiding tipping when the L-shaped frame is rotated. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0017] Figure 1 This is a schematic diagram of the three-dimensional structure of a fixing device according to an embodiment of the present application;

[0018] Figure 2 This is a schematic diagram of the meshing structure of bevel gear 1 and bevel gear 2 of the present invention;

[0019] Figure 3 This is a three-dimensional schematic diagram of the support bar structure of the utility model;

[0020] Figure 4 It is a schematic diagram of the three-dimensional structure of the clamping plate second structure of the present utility model.

[0021] In the figure: 1. Blade body; 2. Clamping plate 1; 3. L-shaped frame; 4. Support plate; 5. Base; 6. Hydraulic cylinder; 7. Bevel gear 1; 8. Extension plate; 9. Bevel gear 2; 10. Motor; 11. Connecting plate 1; 12. Connecting plate 2; 13. Connecting piece; 14. Support bar; 15. Clamping plate 2; 16. Auxiliary plate; 17. Positioning plate 1; 18. Limiting bar; 19. Fixed plate; 20. Positioning plate 2; 21. Telescopic rod; 22. Vertical plate. DETAILED DESCRIPTION

[0022] In order to make the purpose, features, and advantages of this application more obvious and easy to understand, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the embodiments described below are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0023] Example 1

[0024] Reference Figure 1-Figure 4, a fixing device for processing aircraft engine blades includes a base 5, the top of the base 5 is fixedly connected to a support plate 4, the top of the support plate 4 is provided with a clamping mechanism, the clamping mechanism includes a clamping plate 2, a hydraulic cylinder 6 and a vertical plate 22, one side of the clamping plate 2 is fixedly connected to a positioning plate 20, the top of the positioning plate 20 is fixedly connected to the vertical plate 22, one side of the vertical plate 22 is fixedly connected to a telescopic rod 21, one end of the telescopic rod 21 is fixedly connected to an auxiliary plate 16, one side of the auxiliary plate 16 is overlapped with a blade body 1, the bottom of the blade body 1 is engaged with a limiting strip 18, the bottom of the limiting strip 18 is fixedly connected to a fixing plate 19, one side of the fixing plate 19 is fixedly connected to the clamping plate 2, the other side of the blade body 1 is overlapped with a positioning plate 17, one side of the positioning plate 17 is fixedly connected to the clamping plate 2 15, one side of the clamping plate 2 15 is fixedly connected to the hydraulic cylinder 6, the bottom of the hydraulic cylinder 6 is fixedly connected to a connecting plate 11, the bottom of the connecting plate 11 is fixedly connected to an L-shaped frame 3, and one side of the L-shaped frame 3 is fixedly connected to the connecting plate 2 12;

[0025] The second clamping plate 15 can be used to connect the hydraulic cylinder 6 with the positioning plate 17, thereby adjusting the use position of the positioning plate 17 to achieve the clamping and fixing of the blade body 1. The fixing plate 19 can be used to support the bottom of the limit bar 18. The limit bar 18 can be used to guide the initial insertion of the blade body 1. The vertical plate 22 can be connected to the auxiliary plate 16 by the telescopic rod 21. The auxiliary plate 16 can apply a force to one side of the blade body 1, thereby improving the fitting effect of the blade body 1 and the positioning plate 17, reducing the shaking of the blade body 1 between the positioning plate 17 and the second positioning plate 20. At the same time, the auxiliary plate 16, the positioning plate 17 and the second positioning plate 20 can increase the contact area between the clamping structure and the blade body 1, thereby improving the stability of the blade body 1 when clamping.

[0026] One side of the L-shaped frame 3 is fixedly connected to a connecting piece 13, one end of which is rotatably connected to a support frame, the bottom of the support frame is fixedly connected to the support plate 4, and a bevel gear 7 is inserted through the outside of the other connecting piece 13. A bevel gear 2 9 is engaged with one side of the bevel gear 7, and one side of the bevel gear 2 9 is fixedly connected to the output shaft of the motor 10. One side of the motor 10 is fixedly connected to an auxiliary frame, the bottom of the auxiliary frame is fixedly connected to the support plate 4, and one side of the auxiliary frame is rotatably connected to the bevel gear 2 9. A support bar 14 is fixedly connected to the top of the support plate 4, and the top of the support bar 14 overlaps the L-shaped frame 3. An extension plate 8 is slidably connected to one side of the base 5, and a mounting hole is provided on the top of the extension plate 8;

[0027] Specifically, the connecting piece 13 can be used to assist in connecting one side of the L-shaped frame 3 with the external structure, and the supporting frame can be used to support one side of the L-shaped frame 3 to facilitate the stable rotation of the L-shaped frame 3 on the top of the support plate 4. The auxiliary frame can be used to support and reinforce the motor 10 and the bevel gear 2 9. The motor 10 can drive the bevel gear 2 9 to rotate. The engagement of the bevel gear 2 9 with the bevel gear 1 7 can provide power for the rotation of the bevel gear 1 7, thereby realizing the rotation adjustment of the L-shaped frame 3 and the blade body 1, changing the fixed direction of the blade body 1 on the top of the support plate 4, and using the base 5 to support and reinforce the bottom of the support plate 4. The through hole opened at the top of the support plate 4 can reduce the motion interference of the connecting plate 11 and the hydraulic cylinder 6 during rotation. The position adjustment of the extension plate 8 can assist in the installation and reinforcement of the base 5.

[0028] The use process of the fixing device for machining aircraft engine blades provided by the utility model is as follows:

[0029] Working principle: First, place the blade body 1 between the positioning plate 20 and the positioning plate 1 17. The bottom of the blade body 1 is engaged in the limiting strip 18. At this time, one side of the auxiliary plate 16 overlaps with the blade body 1 and applies force to one side of the blade body 1. Then, the hydraulic cylinder 6 is used to drive the clamping plate 2 15 and the positioning plate 1 17 to move to the side close to the blade body 1 and overlap with one side of the blade body 1. At this time, the positioning plate 20 and the positioning plate 1 17 are used to quickly clamp the blade body 1. The blade body 1 can be processed and processed. When the blade body needs to be changed 1, the motor 10 is used to drive the bevel gear 2 9 to rotate, and the bevel gear 2 9 drives the bevel gear 1 7 to rotate, so that the connecting piece 13 and the L-shaped frame 3 rotate synchronously. At this time, the L-shaped frame 3 and the connecting plate 1 11 rotate 90° clockwise with the axis of the connecting piece 13 as the center of the circle until the bottom of the L-shaped frame 3 overlaps with the support plate 4, and the connecting plate 1 11 passes through the through hole on the support plate 4. At this time, the blade body 1 is placed horizontally. At this time, the extension plates 8 are moved on both sides of the base 5, and the extension plates 8 and the installation position are connected with bolts to realize the installation and fixation of the entire device.

[0030] The preferred embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The preferred embodiments do not describe all details in detail, nor do they limit the present invention to the specific embodiments described. Obviously, many modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A fixture for machining aircraft engine blades, characterized by: The invention comprises a base (5), the top of the base (5) is fixedly connected to a support plate (4), the top of the support plate (4) is provided with a clamping mechanism, the clamping mechanism comprises a clamping plate (2), a hydraulic cylinder (6) and a vertical plate (22), one side of the clamping plate (2) is fixedly connected to a positioning plate (20), the top of the positioning plate (20) is fixedly connected to the vertical plate (22), one side of the vertical plate (22) is fixedly connected to a telescopic rod (21), one end of the telescopic rod (21) is fixedly connected to an auxiliary plate ( 16), one side of the auxiliary plate (16) is overlapped with the blade body (1), the bottom of the blade body (1) is engaged with a limit strip (18), the bottom of the limit strip (18) is fixedly connected with a fixed plate (19), one side of the fixed plate (19) is fixedly connected to the clamping plate 1 (2), the other side of the blade body (1) is overlapped with a positioning plate 1 (17), one side of the positioning plate 1 (17) is fixedly connected to the clamping plate 2 (15), and one side of the clamping plate 2 (15) is fixedly connected to the hydraulic cylinder (6).

2. The fixture for machining an aircraft engine blade according to claim 1, characterized in that: The bottom of the hydraulic cylinder (6) is fixedly connected to a connecting plate 1 (11), the bottom of the connecting plate 1 (11) is fixedly connected to an L-shaped frame (3), and one side of the L-shaped frame (3) is fixedly connected to a connecting plate 2 (12).

3. The fixture for machining an aircraft engine blade according to claim 2, characterized in that: One side of the L-shaped frame (3) is fixedly connected to a connecting piece (13), one end of one of the connecting pieces (13) is rotatably connected to a support frame, and the bottom of the support frame is fixedly connected to the support plate (4).

4. The fixture for machining an aircraft engine blade according to claim 3, characterized in that: A bevel gear 1 (7) is inserted through the outside of the other connecting member (13), one side of the bevel gear 1 (7) is meshed with a bevel gear 2 (9), and one side of the bevel gear 2 (9) is fixedly connected to the output shaft of the motor (10).

5. The fixing device for machining an aircraft engine blade according to claim 4, characterized in that: One side of the motor (10) is fixedly connected to an auxiliary frame, the bottom of the auxiliary frame is fixedly connected to the support plate (4), and one side of the auxiliary frame is rotationally connected to the second bevel gear (9).

6. The fixture for machining an aircraft engine blade according to claim 1, characterized in that: A support bar (14) is fixedly connected to the top of the support plate (4), and the top of the support bar (14) overlaps the L-shaped frame (3).

7. The fixture for machining an aircraft engine blade according to claim 1, characterized in that: An extension plate (8) is slidably connected to one side of the base (5), and a mounting hole is provided on the top of the extension plate (8).

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