CN216502429U

CN216502429U - Aeroengine annular spare part processing is with tight mould that rises

Info

Publication number: CN216502429U
Application number: CN202123395118.3U
Authority: CN
Inventors: 臧怀庆; 马乐
Original assignee: Shenyang Xindafang Power Equipment Co ltd
Current assignee: Shenyang Xindafang Power Equipment Co ltd
Priority date: 2021-12-31
Filing date: 2021-12-31
Publication date: 2022-05-13
Anticipated expiration: 2031-12-31

Abstract

The utility model discloses a tensioning clamping fixture for processing annular parts of an aircraft engine, which relates to the technical field of aviation part processing equipment and comprises a disc-shaped workbench, wherein a support ring is coaxially arranged on the upper surface of the workbench, a working box is slidably arranged in the support ring, a tensioning structure is arranged on the working box, the tensioning structure comprises a motor, a rotating shaft, a driving bevel gear, a plurality of driven bevel gears, a plurality of screw rods, a plurality of push plates and a plurality of U-shaped plates, a cavity is arranged in the working box, the motor is arranged at the central position in the cavity of the working box, and the rotating shaft movably penetrates through the central position of the upper surface of the working box; the clamping device can be used for tensioning and clamping the annular part, and external force is uniformly applied from inside to outside, so that the part is prevented from being damaged by the clamp, the contact area between the clamping device and the annular part is increased, the friction force is increased, the clamping is more stable, and the processing quality is improved.

Description

Aeroengine annular spare part processing is with tight mould that rises

Technical Field

The utility model relates to the technical field of aviation part processing equipment, in particular to a tensioning clamping fixture for processing an annular part of an aero-engine.

Background

In aeroengine spare part, some parts are the annular structure to need process its surface, but current device generally adopts the mode of edge centre gripping to annular part centre gripping, can lead to annular part's deformation or surface damage during processing, and the centre gripping is unstable, drops easily, seriously influences processingquality, so an aeroengine annular spare part processing is with tight mould that rises urgently awaits developing.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects in the prior art, the utility model provides the tensioning clamping fixture for processing the annular part of the aircraft engine, which can perform tensioning clamping on the annular part, and uniformly apply external force from inside to outside, so that the part is prevented from being damaged by the clamping fixture, the contact area between the annular part and the clamping fixture is increased, the friction force is increased, the clamping is more stable, and the processing quality is improved.

In order to realize the purpose, the utility model is realized by the following technical scheme: a tensioning clamping fixture for machining annular parts of an aircraft engine comprises a disc-shaped workbench, wherein a support ring is coaxially arranged on the upper surface of the workbench, a working box is arranged in the support ring in a sliding manner, a tensioning structure is arranged on the working box and comprises a motor, a rotating shaft, a driving bevel gear, a plurality of driven bevel gears, a plurality of lead screws, a plurality of push plates and a plurality of U-shaped plates, a cavity is formed in the working box, the motor is arranged at the central position in the cavity of the working box, the rotating shaft movably penetrates through the central position on the upper surface of the working box, the lower end of the rotating shaft is connected with the output end of the motor, the upper end of the rotating shaft is connected with the driving bevel gear, a plurality of vertical fixing plates are uniformly arranged on a circle of the upper surface of the working box, close to the edge, the center of the inner side of each fixing plate is rotatably connected with one end of the corresponding lead screw, and the other end of the lead screw is connected with the driven bevel gear, the driving bevel gear is meshed with the driven bevel gear at an angle of 90 degrees, two sides of the center of the fixing plate are provided with limiting holes, two ends of the U-shaped plate movably penetrate through the limiting holes, the center of the U-shaped plate is provided with a threaded hole, the screw rod is screwed in the threaded hole of the U-shaped plate, and the U-shaped plate corresponding to the outer side of the fixing plate is fixedly connected with the push plate.

Preferably, a position of the workbench corresponding to a position between each fixing plate and the driven bevel gear is provided with a limiting plate, and the screw rod movably penetrates through the limiting plate.

Preferably, the outer side wall of the push plate is a curved surface matched with the radian of the inner side surface of the annular part to be processed, and the outer side wall is provided with a rubber pad.

Preferably, four sliding blocks are uniformly arranged on the side wall of the working box, sliding grooves corresponding to the four sliding blocks are formed in the inner wall of the supporting ring, and the sliding blocks are connected with the sliding grooves in a sliding mode.

Preferably, the through-hole has been seted up to workstation central point, bottom surface central point puts under the workstation and is provided with the cylinder, the flexible end activity of cylinder runs through in the through-hole, and the flexible end of cylinder puts fixed connection with bottom surface central point under the work box.

Preferably, the bottom surface is provided with the supporting leg under the workstation.

The utility model provides a tensioning clamping fixture for processing annular parts of an aircraft engine, which has the following beneficial effects:

1. the clamping device can be used for tensioning and clamping the annular part, and external force is uniformly applied from inside to outside, so that the part is prevented from being damaged by the clamp, the contact area between the clamping device and the annular part is increased, the friction force is increased, the clamping is more stable, and the processing quality is improved;

2. the rubber pad can prevent the push plate from directly contacting the annular part to damage the annular part, increase the friction force between the push plate and the part and improve the clamping stability; the height of the tensioning structure can be adjusted through the air cylinder, so that tensioning of different positions of the inner ring of the annular part is met.

Drawings

FIG. 1 is a top sectional view of the present invention.

FIG. 2 is a front sectional view of the present invention.

Fig. 3 is a partially enlarged view of fig. 1 of the present invention.

In the figure: 1. a work table; 2. supporting legs; 3. a support ring; 4. a cylinder; 5. a work box; 6. a cavity; 7. a motor; 8. a rotating shaft; 9. a drive bevel gear; 10. a driven bevel gear; 11. a screw rod; 12. a fixing plate; 13. an annular part; 14. a threaded hole; 15. a U-shaped plate; 16. a rubber pad; 17. pushing the plate; 18. a limiting hole; 19. a chute; 20. a slider; 21. and a limiting plate.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in fig. 1-3, a tensioning clamping fixture for processing annular parts of an aircraft engine comprises a disc-shaped workbench 1, wherein a support ring 3 is coaxially installed on the upper surface of the workbench 1, a working box 5 is slidably arranged in the support ring 3, a tensioning structure is arranged on the working box 5, the tensioning structure comprises a motor 7, a rotating shaft 8, a driving bevel gear 9, a plurality of driven bevel gears 10, a plurality of lead screws 11, a plurality of push plates 17 and a plurality of U-shaped plates 15, a cavity 6 is arranged in the working box 5, the motor 7 is arranged at the central position in the cavity 6 of the working box 5, the rotating shaft 8 movably penetrates through the central position of the upper surface of the working box 5, the lower end of the rotating shaft 8 is connected with the output end of the motor 7, the upper end of the rotating shaft is connected with the driving bevel gear 9, a plurality of vertical fixing plates 12 are uniformly installed on a circle of the upper surface of the working box 5 close to the edge, the center of the inner side of each fixing plate 12 is rotatably connected with one end of a corresponding screw rod 11, the other end of each screw rod 11 is connected with a driven bevel gear 10, the driving bevel gear 9 and the driven bevel gear 10 are in 90-degree meshed connection, two sides of the center of each fixing plate 12 are provided with limiting holes 18, two ends of each U-shaped plate 15 movably penetrate through the limiting holes 18, the center of each U-shaped plate 15 is provided with a threaded hole 14, each screw rod 11 is rotatably connected into the threaded hole 14 of each U-shaped plate 15, and the U-shaped plate 15 corresponding to the outer side of each fixing plate 12 is fixedly connected with a push plate 17; a position limiting plate 21 is arranged on the workbench 1 corresponding to a position between each fixing plate 12 and the driven bevel gear 10, and the screw rod 11 movably penetrates through the limiting plate 21; the outer side wall of the push plate 17 is a curved surface matched with the radian of the inner side surface of the annular part 13 to be processed, and the outer side wall is provided with a rubber pad 16; four sliding blocks 20 are uniformly arranged on the side wall of the working box 5, sliding grooves 19 corresponding to the four sliding blocks 20 are formed in the inner wall of the supporting ring 3, and the sliding blocks 20 are in sliding connection with the sliding grooves 19; a through hole is formed in the center of the workbench 1, an air cylinder 4 is arranged in the center of the lower bottom surface of the workbench 1, the telescopic end of the air cylinder 4 movably penetrates through the through hole, and the telescopic end of the air cylinder 4 is fixedly connected with the center of the lower bottom surface of the working box 5; and a support leg 2 is arranged on the lower bottom surface of the workbench 1.

The detailed connection means is a technique known in the art, and the following main description is provided for the working principle and process, and specifically provided for the following:

the motor 7 and the cylinder 4 are connected with an external electric control system through wires.

As can be seen from the attached figures 1-3 in the specification, when the device works, firstly, an annular part 13 to be processed is vertically placed on a support ring 3, and the height of a working box 5 can be adjusted through a cylinder 4 on the lower bottom surface of a working table 1 according to the height of the annular part 13, so that a tensioning structure is aligned with a certain height of the inner wall of the annular part 13; the specific regulation is for running through 4 flexible ends of cylinder in workstation 1 center promote the mounting box and reciprocate, because slider 20 that the mounting box lateral wall evenly set up and the spout 19 sliding connection that the inner wall of support ring 3 set up, consequently make the tight structure that rises on work box 5 and the work box 5 reciprocate more stably.

After the height adjustment of the tensioning structure is completed, the motor 7 is started, the output end of the motor 7 rotates to drive the rotating shaft 8 to rotate, the rotating shaft 8 drives the driving bevel gear 9 to rotate, the driving bevel gear 9 is meshed with the driven bevel gear 10 to drive the driven bevel gear 10 to rotate, the screw rod 11 is rotatably connected with the fixed plate 12 and the limiting plate 21, the driven bevel gear 10 drives the screw rod 11 to rotate, the central threaded hole 14 of the U-shaped plate 15 is rotatably connected with the screw rod 11, and the U-shaped plate 15 is movably connected with the limiting hole 18 of the fixed plate 12, so that the screw rod 11 rotates to drive the U-shaped plate 15 to move, and further drive the push plates 17 connected with the U-shaped plate 15 to move, and the driving bevel gear 9 is meshed with the driven bevel gears 10 at the same time, so that one motor 7 can drive the plurality of push plates 17 to move outwards together to correct and clamp the annular part 13 to fix the annular part, not only prevent the damage that causes the part to the outside centre gripping of anchor clamps, a plurality of push pedals 17 simultaneously and the inner wall contact of annular part 13 moreover, increase frictional force makes the centre gripping more stable, promotes processingquality, and rubber pad 16 also increases the frictional force with the part simultaneously, promotes the stability of centre gripping.

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

Claims

1. The tensioning clamping fixture for machining the annular part of the aero-engine comprises a disc-shaped workbench (1) and is characterized in that a support ring (3) is coaxially installed on the upper surface of the workbench (1), a working box (5) is slidably arranged in the support ring (3), a tensioning structure is arranged on the working box (5), the tensioning structure comprises a motor (7), a rotating shaft (8), a driving bevel gear (9), a plurality of driven bevel gears (10), a plurality of lead screws (11), a plurality of push plates (17) and a plurality of U-shaped plates (15), a cavity (6) is formed in the working box (5), the motor (7) is arranged at the central position in the cavity (6) of the working box (5), the rotating shaft (8) movably penetrates through the central position of the upper surface of the working box (5), and the lower end of the rotating shaft (8) is connected with the output end of the motor (7), the upper end is connected with a driving bevel gear (9), a plurality of vertical fixing plates (12) are uniformly installed on a circle, close to the edge, of the upper surface of the working box (5), the inner side center of each fixing plate (12) is rotatably connected with one end of a corresponding screw rod (11), the other end of each screw rod (11) is connected with a driven bevel gear (10), the driving bevel gear (9) and the driven bevel gear (10) are in 90-degree angle engagement connection, limiting holes (18) are formed in two sides of the center of each fixing plate (12), two ends of each U-shaped plate (15) movably penetrate through the limiting holes (18), threaded holes (14) are formed in the center of each U-shaped plate (15), the screw rods (11) are rotatably connected into the threaded holes (14) of the U-shaped plates (15), and the U-shaped plates (15) outside the corresponding fixing plates (12) are fixedly connected with the push plates (17).

2. The tensioning clamping fixture for machining the annular part of the aircraft engine according to claim 1, wherein a limiting plate (21) is mounted on the workbench (1) corresponding to a position between each fixing plate (12) and the driven bevel gear (10), and the screw rod (11) movably penetrates through the limiting plate (21).

3. The tensioning clamping fixture for machining the annular part of the aircraft engine as claimed in claim 1, wherein the outer side wall of the push plate (17) is a curved surface matched with the radian of the inner side surface of the annular part (13) to be machined, and the outer side wall is provided with a rubber pad (16).

4. The tensioning clamping fixture for machining the annular part of the aircraft engine as claimed in claim 1, wherein four sliding blocks (20) are uniformly arranged on the side wall of the working box (5), sliding grooves (19) corresponding to the four sliding blocks (20) are formed in the inner wall of the support ring (3), and the sliding blocks (20) are slidably connected with the sliding grooves (19).

5. The tensioning clamping fixture for machining the annular part of the aircraft engine as claimed in claim 1, wherein a through hole is formed in the center of the workbench (1), a cylinder (4) is arranged in the center of the lower bottom surface of the workbench (1), the telescopic end of the cylinder (4) movably penetrates through the through hole, and the telescopic end of the cylinder (4) is fixedly connected with the center of the lower bottom surface of the working box (5).

6. The tensioning clamping fixture for machining the annular part of the aircraft engine as claimed in claim 1, wherein the lower bottom surface of the workbench (1) is provided with supporting legs (2).