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Blade-repairing type repair method of engine blade

An engine blade and repair method technology, applied in the directions of aircraft parts, transportation and packaging, can solve the problems of complex process and high cost, and achieve the effects of improving repair quality, improving accuracy and reducing cost

Inactive Publication Date: 2018-08-07
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Aiming at the above-mentioned problems such as complicated repair process and high cost, the present invention proposes a patch repair method for engine blades. By designing a special patch geometry and combining corresponding technological measures, the welding process for forming welded joints is simplified and can Prevent defects and deformation of the front and rear edges, and the joint form is suitable for other fusion welding methods, such as argon arc welding, plasma welding, laser welding, etc., which can greatly reduce repair costs and improve joint quality and stability

Method used

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  • Blade-repairing type repair method of engine blade
  • Blade-repairing type repair method of engine blade
  • Blade-repairing type repair method of engine blade

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Experimental program
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Effect test

Embodiment 1

[0044] If the leading edge corners of multiple blades of an integral blisk are damaged, a unified cutting position including the largest damage is selected, and after the damage is cut along the straight line from the blade tip to the leading edge, the patch design is performed to form a single-sided groove. According to the profile processing welding tool, the profile tolerance is processed according to -0.3mm, the blade and patch are assembled on the welding tool, and the arc welding method is used for welding. Use the welding robot to teach the welding trajectory, followed by repair welding. The tooling is removed after welding, and there is a small gap between the patch and the tooling, which is equivalent to the amount of pre-deformation. X-ray inspection was carried out on the repair welding, and no defects such as pores were found.

Embodiment 2

[0046] The trailing edge of a certain blade was damaged due to processing errors. After the damage was cut along the straight line from the tip to the trailing edge, a patch design was carried out. The curvature of the cut surface was large, and the arc-shaped plate was used to reduce the welding thickness. The welding tooling is processed according to the surface tolerance -0.2mm. After the blades and patches are assembled on the welding tooling, the welding robot is used to teach the welding trajectory, and the welding is performed with uniform welding parameters.

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Abstract

The invention relates to a blade-repairing type repair method of an engine blade. The method comprises the steps that a patch is designed according to the cross-section shape of a removed blade, a groove is processed in the patch section, and a welding fixture is designed according to the shape of the patch, and a welding experiment is carried out on a locally simulated blade to obtain the best welding parameters; and the blade to be repaired and the patch are then welded formally. The molded surface of the groove corresponds to the upper and lower surfaces of the blade, and full-cover and half-cover grooves can be used to form an equal-thickness curved seam. The blade-repairing type repair method of the engine blade simplifies the welding process for forming a welded joint and prevents defects and deformation of the front and rear edges, the welded joint form is applicable to other welding methods, such as argon arc welding, plasma welding, laser welding and the like, the repair costcan be greatly reduced, and the welded joint quality and stability are improved.

Description

technical field [0001] The invention relates to a patch type repair method, which belongs to the field of welding technology. Background technique [0002] Fans and compressors are the key components of aviation turbojet engines. Their main function is to increase the pressure of the air used as the working medium of the engine. Among them, the rotor blades are moving parts rotating at high speed. They are large in number, thin in shape, harsh in condition, and complex in working environment. It has always been one of the components with the highest failure rate in engine use and experiments. Repairing the damaged blades before using them can reduce the life-cycle cost of the engine. Especially at present, with the increasing demand for the use of blisks, the need for repairing rotor blades is more urgent. This is because the blisks are an integrated structure, which makes it difficult to replace damaged blades. Therefore, corresponding repair technologies are necessary to ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00
CPCB23P6/002B23P2700/01
Inventor 万晓慧金俊龙郭德伦李晓红
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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