CN216577573U

CN216577573U - Multi-angle overturning fixture for aero-engine production

Info

Publication number: CN216577573U
Application number: CN202123449639.2U
Authority: CN
Inventors: 陈红芳; 陈罗丹
Original assignee: Zhejiang Xingjian Industrial Automation Co ltd
Current assignee: Zhejiang Xingjian Industrial Automation Co ltd
Priority date: 2021-12-30
Filing date: 2021-12-30
Publication date: 2022-05-24
Anticipated expiration: 2031-12-30

Abstract

The utility model discloses a multi-angle overturning clamp for aircraft engine production, which comprises a bottom plate, wherein a slide rail and a rack are arranged in the middle of the top surface of the bottom plate, a slide seat is slidably arranged on the upper side of the slide rail, a vertical plate and a first motor are fixed on the upper side of the slide seat, a movable plate is fixed on the top end of the vertical plate, a first gear is arranged at the driving end of the first motor, and the first gear and the rack are meshed with each other; the utility model discloses a set up first clamp ring, second clamp ring and fixture, can realize convenient stable centre gripping to aeroengine to realize angle modulation at a plurality of angle within ranges, thereby the convenience is installed the spare part at each position of aeroengine.

Description

Multi-angle overturning fixture for aero-engine production

Technical Field

The utility model relates to an aeroengine production technical field especially relates to an aeroengine production is with multi-angle upset anchor clamps.

Background

The aircraft engine is a highly complex and precise thermodynamic machine, is used as the heart of an aircraft, is not only the power for the flight of the aircraft, but also an important driving force for promoting the development of the aviation industry, and each important change in the human aviation history is inseparable from the technical progress of the aircraft engine. The parts on the aircraft engine are numerous, and in the production and assembly process, the aircraft engine needs to be fixedly supported by using a clamp, so that various parts are convenient to assemble.

In the prior art, the clamp used for the aircraft engine generally has the following defects in actual use: when anchor clamps were to aeroengine's angular adjustment, the control range was limited, consequently inconvenient part to each position was assembled, consequently the utility model provides a multi-angle upset anchor clamps are used in aeroengine production here.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defect that exists among the prior art, and the multi-angle upset anchor clamps are used in aeroengine production that provide.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a multi-angle overturning clamp for production of an aircraft engine comprises a bottom plate, wherein a slide rail and a rack are installed in the middle of the top surface of the bottom plate, a slide seat is installed on the upper side of the slide rail in a sliding mode, a vertical plate and a first motor are fixed on the upper side of the slide seat, a moving plate is fixed at the top end of the vertical plate, a first gear is installed at the driving end of the first motor, and the first gear is meshed with the rack;

an upright post is installed on one side of the top surface of the bottom plate, a supporting plate is installed on the other side of the top surface of the bottom plate, a supporting sleeve ring is fixed at the upper end of the upright post, a second motor is installed in the middle of the upright post, a second gear is installed at the driving end of the second motor, a first clamping ring is slidably arranged on the inner side of the supporting sleeve ring, a toothed ring is fixed on the outer wall of the first clamping ring, the toothed ring is meshed with the second gear, and a plurality of clamping mechanisms are installed on the first clamping ring at equal intervals;

the top of backup pad is rotated through the pivot and is installed the second clamp ring, a plurality of fixture are installed to the equidistant of second clamp ring, the worm wheel is installed to the one end of pivot, the third motor is installed on the top of backup pad, the worm is installed to the drive end of third motor, worm and worm wheel intermeshing.

Further, fixture includes threaded rod, slide bar and splint, the knob is installed to the one end of threaded rod, and the other end rotates the installation with splint, the stopper is installed to the one end of slide bar, the other end and splint fixed mounting, first clamp ring and second clamp ring all run through set up threaded hole and slide opening.

Further, the rubber pad is all installed to the one side of keeping away from threaded rod and slide bar of splint.

Furthermore, six clamping mechanisms are installed on the first clamping ring in total, and six clamping mechanisms are installed on the second clamping ring in total.

Furthermore, two sliding rings are symmetrically installed on the outer side wall of the first clamping ring, and the first clamping ring is installed with the supporting lantern ring in a sliding mode through the sliding rings.

Furthermore, the second motor is fixedly installed with the middle part of the upright post through the transverse plate.

Compared with the prior art, the beneficial effects of the utility model reside in that:

1. the utility model discloses a set up first clamp ring and fixture and can realize the centre gripping to aeroengine to make its axial within range internal rotation at first clamp ring, thereby make things convenient for the installation of spare part.

2. The utility model discloses a set up second clamp ring and fixture and can realize the centre gripping to aeroengine to make it and second clamp ring be together at vertical plane within range internal rotation, thereby make things convenient for the installation of spare part.

To sum up, the utility model discloses a set up first clamp ring, second clamp ring and fixture, can realize convenient stable centre gripping to aeroengine to realize angle modulation at a plurality of angle within ranges, thereby the convenience is installed the spare part at each position of aeroengine.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention.

FIG. 1 is a structural diagram illustrating a state structure of a multi-angle turnover fixture for aircraft engine production according to the present invention;

FIG. 2 is a structural schematic diagram of a state two of the multi-angle turnover fixture for aircraft engine production according to the present invention;

FIG. 3 is a schematic structural view of a first clamp ring of the present invention;

fig. 4 is an installation diagram of the clamping mechanism and the second clamping ring of the present invention.

In the figure: the device comprises a base plate 1, a sliding rail 2, a sliding seat 3, a vertical plate 4, a moving plate 5, a first motor 6, a first gear 7, a rack 8, a vertical column 9, a support lantern ring 10, a first clamping ring 11, a second motor 12, a second gear 13, a toothed ring 14, a clamping mechanism 15, a second clamping ring 16, a rotating shaft 17, a support plate 18, a worm gear 19, a third motor 20, a worm 21, a sliding ring 22, a threaded rod 23, a sliding rod 24 and a clamping plate 25.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Referring to fig. 1-4, the multi-angle turnover fixture for the production of the aircraft engine comprises a bottom plate 1, wherein a slide rail 2 and a rack 8 are installed in the middle of the top surface of the bottom plate 1, a slide seat 3 is installed on the upper side of the slide rail 2 in a sliding manner, a vertical plate 4 and a first motor 6 are fixed on the upper side of the slide seat 3, a movable plate 5 is fixed on the top end of the vertical plate 4, a first gear 7 is installed at the driving end of the first motor 6, and the first gear 7 is meshed with the rack 8;

the aero-engine is firstly hoisted and placed on the moving plate 5, then the first gear 7 is driven by the first motor 6 to be meshed with the rack 8, so that the moving plate 5 and the aero-engine are controlled to move, and the aero-engine is conveyed to positions above two sides of the bottom plate 1.

An upright post 9 is installed on one side of the top surface of the bottom plate 1, a supporting plate 18 is installed on the other side of the top surface of the bottom plate, a supporting sleeve ring 10 is fixed at the upper end of the upright post 9, a second motor 12 is installed in the middle of the upright post 9, a second gear 13 is installed at the driving end of the second motor 12, a first clamping ring 11 is arranged on the inner side of the supporting sleeve ring 10 in a sliding mode, a toothed ring 14 is fixed on the outer wall of the first clamping ring 11, the toothed ring 14 is meshed with the second gear 13, and a plurality of clamping mechanisms 15 are installed on the first clamping ring 11 at equal intervals;

when the moving plate 5 sends the aircraft engine to the middle part of the first clamping ring 11, the aircraft engine is clamped and fixed through the clamping mechanism 15. The second motor 12 drives the second gear 13 to be meshed with the gear ring 14, so that the rotation angle of the first clamping ring 11 and the aircraft engine along the axis of the first clamping ring 11 is controlled, and the assembly of parts of the aircraft engine is facilitated.

The top end of the supporting plate 18 is rotatably provided with a second clamping ring 16 through a rotating shaft 17, the second clamping ring 16 is provided with a plurality of clamping mechanisms 15 at equal intervals, one end of the rotating shaft 17 is provided with a worm wheel 19, the top end of the supporting plate 18 is provided with a third motor 20, the driving end of the third motor 20 is provided with a worm 21, and the worm 21 and the worm wheel 19 are meshed with each other.

When the moving plate 5 sends the aircraft engine to the middle of the second clamping ring 16, the aircraft engine is clamped and fixed through the clamping mechanism 15. The third motor 20 drives the worm 21 to mesh with the worm wheel 19, so as to control the rotation angle of the second clamping ring 16 and the aircraft engine along the axis of the rotating shaft 17, and fig. 2 is a schematic diagram of the second clamping ring 16 during rotation, so that the components of the aircraft engine can be assembled conveniently.

In the invention, the clamping mechanism 15 comprises a threaded rod 23, a sliding rod 24 and a clamping plate 25, wherein one end of the threaded rod 23 is provided with a knob, the other end of the threaded rod 23 is rotatably installed with the clamping plate 25, one end of the sliding rod 24 is provided with a limiting block, the other end of the sliding rod 24 is fixedly installed with the clamping plate 25, and both the first clamping ring 11 and the second clamping ring 16 are provided with a threaded hole and a sliding hole in a penetrating way. Rubber pads are arranged on one side of the clamping plate 25 far away from the threaded rod 23 and the sliding rod 24. The rubber pad can increase the friction force during clamping, increase the stability of clamping, and simultaneously avoid causing abrasion to the surface of the aircraft engine.

In the present invention, as shown in fig. 1 and 2, six gripping mechanisms 15 are mounted in total on the first clamp ring 11, and six gripping mechanisms 15 are mounted in common on the second clamp ring 16.

In the present invention, referring to fig. 3, two sliding rings 22 are symmetrically installed on the outer side wall of the first clamping ring 11, and the first clamping ring 11 is slidably installed with the supporting collar 10 through the sliding rings 22.

In the present invention, as shown in fig. 1 and 2, the second motor 12 is fixedly installed with the middle of the upright post 9 through a horizontal plate.

The utility model discloses a set up first clamp ring 11, second clamp ring 16 and fixture 15, can realize convenient stable centre gripping to aeroengine to realize the angle modulation at a plurality of angle within ranges, thereby the convenience is installed the spare part at each position of aeroengine.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The multi-angle overturning clamp for the production of the aircraft engine comprises a bottom plate (1) and is characterized in that a sliding rail (2) and a rack (8) are installed in the middle of the top surface of the bottom plate (1), a sliding seat (3) is installed on the upper side of the sliding seat (2) in a sliding mode, a vertical plate (4) and a first motor (6) are fixed on the upper side of the sliding seat (3), a moving plate (5) is fixed at the top end of the vertical plate (4), a first gear (7) is installed at the driving end of the first motor (6), and the first gear (7) is meshed with the rack (8);

an upright post (9) is installed on one side of the top surface of the bottom plate (1), a supporting plate (18) is installed on the other side of the top surface of the bottom plate, a supporting sleeve ring (10) is fixed to the upper end of the upright post (9), a second motor (12) is installed in the middle of the upright post (9), a second gear (13) is installed at the driving end of the second motor (12), a first clamping ring (11) is arranged on the inner side of the supporting sleeve ring (10) in a sliding mode, a toothed ring (14) is fixed to the outer wall of the first clamping ring (11), the toothed ring (14) is meshed with the second gear (13), and a plurality of clamping mechanisms (15) are installed on the first clamping ring (11) at equal intervals;

the top of backup pad (18) is rotated through pivot (17) and is installed second clamp ring (16), a plurality of fixture (15) are installed to second clamp ring (16) equidistant, worm wheel (19) are installed to the one end of pivot (17), third motor (20) are installed on the top of backup pad (18), worm (21) are installed to the drive end of third motor (20), worm (21) and worm wheel (19) intermeshing.

2. The multi-angle overturning clamp for the aircraft engine production as claimed in claim 1, wherein the clamping mechanism (15) comprises a threaded rod (23), a sliding rod (24) and a clamping plate (25), a knob is installed at one end of the threaded rod (23), the other end of the threaded rod is rotatably installed with the clamping plate (25), a limiting block is installed at one end of the sliding rod (24), the other end of the sliding rod is fixedly installed with the clamping plate (25), and the first clamping ring (11) and the second clamping ring (16) are both provided with a threaded hole and a sliding hole in a penetrating manner.

3. The multi-angle overturning clamp for the production of the aircraft engine is characterized in that rubber pads are mounted on one side of the clamping plate (25) far away from the threaded rod (23) and the sliding rod (24).

4. The multi-angle turnover fixture for the production of the aircraft engine as claimed in claim 2 or 3, wherein the first clamp ring (11) is provided with six clamping mechanisms (15) in total, and the second clamp ring (16) is provided with six clamping mechanisms (15) in total.

5. The multi-angle overturning clamp for the production of the aircraft engine is characterized in that two sliding rings (22) are symmetrically installed on the outer side wall of the first clamping ring (11), and the first clamping ring (11) is slidably installed with the supporting sleeve ring (10) through the sliding rings (22).

6. The multi-angle overturning clamp for the production of the aero-engine as claimed in claim 1, wherein the second motor (12) is fixedly installed with the middle of the upright post (9) through a transverse plate.