Aeroengine case seam allowance size repairing method

An aero-engine and repair method technology, applied in metal material coating process, fusion spraying, coating and other directions, can solve the problems of lack of mature technology and literature, and achieve the effect of reducing thermal stress and preventing local overheating

Inactive Publication Date: 2016-03-16
HARBIN DONGAN ENGINE GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there is no mature process for reference and no literature for reference to the seam repair method for this type of material.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0050] The surface of the front and rear seams of an aero-engine compressor casing is repaired by plasma spraying nickel-aluminum coating process method to repair the dimensional deformation caused by work wear, and the coating thickness after spraying is required to be 0.9mm ~ 1.4mm. The porosity is controlled below 5%, the content of unmelted particles in the coating is not more than 10%, the maximum particle diameter is not more than 60μm; the Vickers hardness of the coating is not less than 120, and the bonding strength is greater than 35MPa. The specific implementation process is as follows:

[0051] (1) Use acetone to degrease and scrub the sprayed surface of the parts until the surface is free of dirt;

[0052] (2) Protect the non-sprayed surface with high temperature resistant tape and special protective tooling;

[0053] (3) Use No. 24 white corundum sand, sandblasting pressure 0.4MPa, sandblasting distance 150mm, angle 60°, sandblasting the sprayed surface, the surfa...

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PUM

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Abstract

The invention relates to an aeroengine case seam allowance size repairing method. The porosity and hardness of a coating and the content of oxides in the coating can be effectively adjusted by controlling the plasma spraying power and the heating process of spraying powder during flying, and heat stress of the coating is reduced. The hardness and thermal expansion coefficient of the prepared nickel-aluminum coating are equivalent with those of a case, the bonding strength of the coating is far higher than the stress strength of a case seam allowance under the given working condition, and the use working condition of the aeroengine case can be met.

Description

technical field [0001] The invention relates to a size repairing method, in particular to a size repairing method for an aero-engine case notch. Background technique [0002] The working conditions of aero-engine parts are harsh, and their parts are prone to wear and tear due to the perennial vibration. During the working process of the aero-engine, due to factors such as materials, structure and working conditions, the accessory drive case made of cast magnesium 5, the compressor case made of No. The wear and deformation of the mouth will cause the rotor and stator to be out of center, and in severe cases, it will lead to the occurrence of eccentric wear failure. In order to meet the requirements of use and solve the eccentric wear fault, it is necessary to repair the matching seam part. The existing repair method is to weld eight points along the circumferential direction of the seam seam of the compressor case. Welding eight points is the method of argon arc welding, su...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/02C23C4/08C23C4/134
CPCC23C4/02C23C4/08
Inventor 宋丙红师玉英解维生周锴司锐张彦飞曲延龙周权贺健
Owner HARBIN DONGAN ENGINE GRP
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