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Aero-engine turbine disc lifting appliance and operation method thereof

An aero-engine and turbine disk technology, which is applied in the aviation field, can solve the problems of high requirements, low efficiency of turbine disk assembly or maintenance, complex structure, etc., and achieves the effects of simple structure, improved assembly or maintenance efficiency, and convenient installation.

Pending Publication Date: 2020-11-06
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the complex structure of the "inner expansion" spreader and high requirements in the operation process, the assembly or maintenance efficiency of the turbine disc is relatively low

Method used

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  • Aero-engine turbine disc lifting appliance and operation method thereof
  • Aero-engine turbine disc lifting appliance and operation method thereof
  • Aero-engine turbine disc lifting appliance and operation method thereof

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Embodiment Construction

[0042] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Apparently, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0043] In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rathe...

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Abstract

The invention relates to an aero-engine turbine disc lifting appliance and an operation method thereof. The aero-engine turbine disc lifting appliance comprises at least two arc-shaped pieces, connecting pieces and a first locking mechanism, the arc-shaped pieces are sequentially connected to form an annular piece, at least one pair of two adjacent arc-shaped pieces are connected through the connecting pieces, at least one connecting positions of the connecting pieces and the arc-shaped pieces can be adjusted so as to adjust the inner diameter of the annular piece, and the first locking mechanism is used for locking the connecting pieces and the arc-shaped pieces after the connecting positions of the connecting pieces and the arc-shaped pieces are adjusted. The lifting appliance is simplein structure and convenient to operate, and can be operated by one person, so that the clamping efficiency of the lifting appliance is improved; and the lifting appliance locking structure is stable and low in loosening risk.

Description

technical field [0001] The invention relates to the field of aviation, in particular to an aero-engine turbine disk spreader and an operating method thereof. Background technique [0002] The turbine disk of an aero-engine is heavy, and there is no special structure on it to cooperate with the crane. During the assembly or maintenance of the turbine disk, it is difficult to move it by hand. Usually, a spreader with an "inward expansion" structure is used. That is: the spreader is set at the position where the turbine shaft is pierced in the middle of the turbine disk by tensioning, and then cooperates with the crane to realize the hoisting and moving of the turbine disk. Due to the complex structure of the "inner expansion" spreader, the requirements are high in the operation process, resulting in relatively low assembly or maintenance efficiency of the turbine disc. Contents of the invention [0003] One of the objectives of the present invention is to provide an aero-en...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B66C1/44
CPCB66C1/44
Inventor 李志平胡一廷史新宇姚星
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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