CN216543112U

CN216543112U - Aeroengine impeller dismounting device

Info

Publication number: CN216543112U
Application number: CN202220093014.2U
Authority: CN
Inventors: 樊夕夕; 牛继超
Original assignee: Jiangxi Zhongfa Tianxin Aero Engine Technology Co ltd
Current assignee: Jiangxi Zhongfa Tianxin Aero Engine Technology Co ltd
Priority date: 2022-01-14
Filing date: 2022-01-14
Publication date: 2022-05-17
Anticipated expiration: 2032-01-14

Abstract

When the impeller needs to be disassembled, the disassembling part penetrates into the cavity of the impeller, the clamping step surface is matched with the step on the inner surface of the cavity of the impeller, the impeller is clamped by the disassembling part, the disassembling part is fixed on the support sleeve through the threaded part, the pull rod is prevented from moving towards the direction of the support sleeve by rotating the pull rod (the rotating direction is the direction of screwing into the support sleeve), the support sleeve can move towards the direction of the pull rod in cooperation with the impeller, the impeller is disassembled, the whole process is smooth, the impeller blade does not need to be knocked, and the shaft hole in the impeller is not easily damaged.

Description

Aeroengine impeller dismounting device

Technical Field

The utility model relates to the field of aero-engines, in particular to an aero-engine impeller dismounting device.

Background

At present, an aircraft engine impeller is originally in clearance fit, the fit mode of the impeller after design change is transition fit, and the impeller is usually manually disassembled in the disassembling process; the manual dismantling is that a worker lifts a centrifugal disc arranged behind the impeller by hand, the impeller is dismantled by the supporting effect of the centrifugal disc on the impeller, the operation has higher requirement on the technical level of the worker, the stress of the centrifugal disc is ensured to be uniform in the dismantling process, and otherwise parts are easy to scratch and even block. When the phenomenon of blocking appears in the dismantlement in-process, can use the rubber hammer to strike the impeller when necessary, lead to easily striking the position and take place deformation, influence aeroengine's performance. When the impeller is removed, the centrifugal disc is also taken out. The process of disassembling the impeller affects the assembly of the centrifugal discs.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a dismounting device for an aircraft engine impeller, which is used for solving the technical problems that the traditional aircraft engine impeller is inconvenient to dismount and is easy to damage the impeller during dismounting.

In order to achieve the purpose, the utility model adopts the technical scheme that: the utility model provides an aeroengine impeller dismounting device, aeroengine impeller dismounting device includes:

the disassembling part is cylindrical, one end of the disassembling part is provided with a clamping step surface, and the clamping step surface is matched with a step on the inner surface of the cavity of the impeller to clamp the impeller;

the support sleeve is connected with the other end of the splitting part through a threaded piece and is provided with a threaded hole;

the pull rod, the pull rod includes screw rod portion and handle portion, the one end of screw rod portion is fixed in on the handle portion, the other end of screw rod portion with screw hole on the support cover cooperatees.

In one embodiment, the splitting part comprises a lower splitting block and an upper splitting block arranged at the upper end of the lower splitting block, the lower splitting block is connected with the upper splitting block through a screw, the clamping step surface is arranged on the lower splitting block, and the upper splitting block is connected with the supporting sleeve.

In one embodiment, the lower split block is made of a copper material.

In one embodiment, the splitting part is composed of a plurality of splitting blocks with the same shape, and each splitting block is independently fixed on the supporting sleeve through a threaded piece.

In one embodiment, the end of the support sleeve not threadedly connected to the break-away portion is a sliding fit on the inner surface of the break-away portion.

In one embodiment, the threaded hole in the support sleeve is disposed in the center of the support sleeve.

In one embodiment, the screw portion of the pull rod is disposed in the middle of the handle portion, and the screw portion is perpendicular to the handle portion.

One or more technical solutions described above in the embodiments of the present invention have at least the following technical effects or advantages:

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an aircraft engine impeller dismounting device provided by an embodiment of the utility model.

Wherein the respective reference numerals are as follows:

1. a support sleeve; 2. splitting; 3. a pull rod; 4. clamping the step surface; 21. disassembling the blocks; 22. and (5) disassembling the split blocks.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the utility model and are not to be construed as limiting the utility model.

In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Referring to fig. 1, an embodiment of the present application provides a dismounting device for an aircraft engine impeller, which includes a dismounting portion 2, a support sleeve 1, and a pull rod 3. The splitting part 2 is cylindrical, a clamping step surface 4 is arranged at one end of the splitting part 2, and the clamping step surface 4 is matched with a step on the inner surface of the cavity of the impeller to clamp the impeller. The support sleeve 1 is connected with the other end of the splitting part 2 through a threaded piece, and a threaded hole is formed in the support sleeve 1. The pull rod 3 comprises a screw rod part and a handle part, one end of the screw rod part is fixed on the handle part, and the other end of the screw rod part is matched with a threaded hole in the support sleeve 1.

When the impeller of the aircraft engine needs to be disassembled, the disassembling part 2 is firstly inserted into the cavity of the impeller, and the clamping step surface 4 is matched with the step on the inner surface of the cavity of the impeller, thereby causing the splitting part 2 to grip the impeller and then fixing the splitting part 2 to the support sleeve 1 by means of screws, by rotating the tie rod 3 (the direction of rotation being the direction of screwing into the interior of the support sleeve 1) and preventing the tie rod 3 from moving towards the support sleeve 1, the supporting sleeve 1 can move towards the pull rod 3 in cooperation with the impeller, so that the impeller is disassembled, the whole process is gentle, the impeller blade does not need to be knocked, the shaft hole on the impeller is not easy to damage, furthermore, the dismounting device for the impeller of the aero-engine, provided by the embodiment of the utility model, can conveniently dismount the impeller and simultaneously avoid damage to the impeller.

In one embodiment, the splitting part 2 comprises a lower splitting block 22 and an upper splitting block 21 arranged at the upper end of the lower splitting block 22, the lower splitting block 22 is connected with the upper splitting block 21 through a screw, the clamping step surface 4 is arranged on the lower splitting block 22, and the upper splitting block 21 is connected with the support sleeve 1. When the impeller of different sizes, the accessible is changed the lower of looks adaptation and is torn open the piecemeal 22 and dismantle, because the lower piece of tearing open 22 and last adoption screw thread spare link to each other between the piece 21 of tearing open, so the dismouting of lower piece 22 is more convenient.

In one embodiment, lower split block 22 is made of a copper material. Compared with steel, the copper ground is softer, so that when the impeller is disassembled by the lower disassembling block 22 made of the copper material, the contact surface of the impeller is not easy to damage.

In one embodiment, the splitting part 2 is composed of a plurality of splitting blocks with the same shape, and each splitting block is independently fixed on the supporting sleeve 1 through a threaded piece. In detail, the splitting part 2 in this embodiment includes three splitting blocks having the same shape. The impeller is clamped independently by dividing the splitting part 2 into three parts, so that the matching surface of the impeller is uniformly stressed.

In one embodiment, the end of the support sleeve 1 not in threaded connection with the break-away portion 2 is a sliding fit on the inner surface of the break-away portion 2. Referring to fig. 1, the bottom of the supporting sleeve 1 is disposed in the splitting part 2 and is in sliding fit with the inner wall of the splitting part 2, so that when the pull rod 3 is rotated, the bottom of the supporting sleeve 1 abuts against the inner surface of the splitting part 2, thereby greatly reducing the shearing force applied to the threaded member connected between the supporting sleeve 1 and the splitting part 2 and avoiding damage to the connecting threaded member between the supporting sleeve 1 and the splitting part 2.

In one embodiment, the threaded hole in the support sleeve 1 is provided in the center of the support sleeve 1. The threaded hole on the support sleeve 1 is arranged in the center of the support sleeve 1, so that the action point of the pulling force given by the pull rod 3 is the center of the support sleeve 1, and the stress of the support sleeve 1 is uniform. The damage of the dismounting device and the impeller caused by uneven stress of the support sleeve 1 is avoided. In one embodiment, the screw portion of the pull rod 3 is disposed in the middle of the handle portion, and the screw portion is perpendicular to the handle portion.

The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aeroengine impeller dismounting device, characterized in that, aeroengine impeller dismounting device includes:

2. An aircraft engine impeller dismounting device according to claim 1, characterized in that:

the split portion including split piece down and set up in split the piece on the last split piece of piece upper end down, split the piece down with it links to each other to adopt the screw thread spare to go up between the split piece, joint step face set up in on the split piece down, go up the split piece with it is connected to support the cover.

3. An aircraft engine impeller dismounting device according to claim 2, characterized in that:

the lower splitting block is made of a copper material.

4. An aircraft engine impeller dismounting device according to claim 1, characterized in that:

the splitting part is composed of a plurality of splitting blocks with the same appearance, and each splitting block is independently fixed on the supporting sleeve through a threaded part.

5. An aircraft engine impeller dismounting device according to claim 1, characterized in that:

one end of the support sleeve, which is not in threaded connection with the splitting part, is in sliding fit with the inner surface of the splitting part.

6. An aircraft engine impeller dismounting device according to claim 1, characterized in that:

the threaded hole on the supporting sleeve is arranged in the center of the supporting sleeve.

7. An aircraft engine impeller dismounting device according to claim 1, characterized in that:

the screw portion of pull rod set up in the middle part of handle portion, just the screw portion with handle portion looks vertically.