A method for removing damaged blades of an aeroengine stator assembly

A technology of aero-engines and blades, which is applied in the direction of electric processing equipment, electrode manufacturing, and auxiliary devices, etc., can solve the problem of not removing damaged blades, and achieve the effect of reducing maintenance costs and high application value

Active Publication Date: 2016-08-17
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the repair work of this type of stator assembly has not been carried out in China, and there is no way to remove the damaged blade.

Method used

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  • A method for removing damaged blades of an aeroengine stator assembly
  • A method for removing damaged blades of an aeroengine stator assembly
  • A method for removing damaged blades of an aeroengine stator assembly

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Effect test

Embodiment Construction

[0022] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0023] A method for removing damaged blades of an aero-engine stator assembly comprises the steps of:

[0024] Step 1: Use wire cutting equipment to remove most of the blade body of the damaged blade 1. During the cutting process, on the premise of not destroying the inner and outer ring blade plates, reduce the residual amount of the blade as much as possible; after the wire cutting is completed, the fan section The remaining blades 13 on the stator assembly have three profiles, which are respectively the residual blades 13 located on the T-shaped blade plate 3, the flow channel blade plate 4 and the large curved edge blade plate 5;

[0025] Step 2: Clamp the segment stator assembly that has been wire-cut into the positioning tool;

[0026] Step 3: Send the segment stator assembly and its positioning tool into the EDM machine tool, ...

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Abstract

The invention discloses a method for removing a damaged blade of a stator component of an aero-engine and belongs to the technical field of aero-engine part maintenance. In the operating process of the engine, partial blades of the stator component have defects such as cracks and damage, a technician wants to repair the stator component, but the stator component repairing work has not been carried out at home and a method for removing the damaged blade is absent. The method fills up a technical blank in the field of stator component repair at home, the damaged blade of the stator component is removed successfully, and a solid foundation is laid for subsequently installing a new blade; moreover, the stator component with the new blade completely meets performance requirement, the stator component is recycled, and compared with the traditional method for maintaining an engine by completely replacing the stator component, the method has the advantages that the maintenance cost of the engine is greatly reduced and the method has high application value.

Description

technical field [0001] The invention belongs to the technical field of aero-engine component maintenance, in particular to a method for removing damaged blades of an aero-engine stator assembly. Background technique [0002] As an important component of an aero-engine, the stator assembly is composed of an inner ring, an outer ring and blades. The blades are connected to the inner ring and the outer ring by vacuum brazing. The inner ring and outer ring are generally made of GH600 alloy, and the blades are generally made of GH4169 alloy. . [0003] During the operation of the engine, it is affected by airflow impact and vibration fatigue. After a period of operation, some blades of the stator assembly will have defects such as cracks and damage. Repair, reduce the scrap rate of stator components, and reduce engine maintenance costs. However, the repair work of this type of stator assembly has not been carried out in China, and there is no method for removing the damaged bla...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23H7/02B23H1/00B23H1/04B23H11/00
CPCB23H1/00B23H1/04B23H7/02B23H11/003
Inventor 谭益广于冰赵文涛钱昆
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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