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Repair method for abrasion of inner wall of engine turbine rear bearing seat

A repair method and technology of turbine bearings, applied in the direction of coating, metal material coating process, etc., to achieve the effect of strong binding force

Inactive Publication Date: 2016-11-16
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention aims at the deficiencies of the above-mentioned prior art, and provides a strong binding force, which is not easy to cause the coating to fall off during the sliding wear process, and will not cause serious wear to the bearing. It adopts new iron-based powder as raw material and laser melting The Method of Restoring the Wear of the Inner Wall of the Engine Turbine Rear Bearing Block by Recovering Technology

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0010] After the aero-engine was overhauled and disassembled, the inner wall of the turbine rear bearing seat was measured to be worn, and the wear amount was 0.3 mm. The iron-based powder provided by the invention was used as the raw material, and the laser cladding equipment with a power of 1kW was used for repair. By weight percentage, powder chemical composition: 0.05% carbon, 19.0% Cr, 7.0% Ni; 5.0% Cu; 0.5 Mn; 1.0% Si; the rest is Fe. The powder particle size is 45 μm. Coaxial powder feeding nozzle laser cladding is adopted, the cladding process parameters are power 400 W, powder feeding rate 3.0% g / min, spot diameter Ф1.0% mm, nozzle scanning speed 8.0% mm, lap rate is 50%, and the single-layer height of cladding is 0.5 mm. Fluorescent and X-ray inspections were performed on the repaired turbine rear bearing seat, and no cracks were found in the metallographic microstructure. Microhardness measurement The hardness of the cladding layer is HV0.1 to 350, reaching 1.0% a...

Embodiment 2

[0012] Aiming at the wear of the inner wall of the turbine rear bearing housing after the overhaul of the aero-engine is measured, and the wear amount is 0.5 mm, the iron-based powder provided by the present invention is used as the raw material, and the laser cladding equipment with a power of 1kW is used for repair. The chemical composition (percentage by weight) of the powder is: 0.07% carbon, 18.0% Cr, 8.0% Ni; 6.0% Cu; 1.0% Mn; 0.6% Si; and the rest is Fe. The particle size of the powder is arbitrarily selected from 45 μm to 105 μm. Coaxial powder feeding nozzle is used for laser cladding, the cladding process parameters are power 500 W, powder feeding rate 4.0% g / min, spot diameter Ф1.2 mm, nozzle scanning speed 10.0% mm, lap rate 50%, the single-layer height of cladding is 0.5 mm. Fluorescence and X-ray inspections were performed on the repaired turbine rear bearing seat, and no cracks were found in the microstructure. Microhardness measurement The hardness of the cla...

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Abstract

The invention provides a repair method for abrasion of the inner wall of an engine turbine rear bearing seat and aims to provide a method that the binding force is high, coating shedding is not prone to being caused in the slidable abrasion process, a bearing cannot be severely abraded, and the abraded inner wall of the bearing seat is repaired. According to the following technical scheme, the repair method can be achieved by comprising the steps that iron-based powder of which the particle size is 45-105 [mu]m and the chemical components comprise 0.05%-0.07% of C, 18.0%-19.0% of Cr, 7.0%-8.0% of Ni, 5.0%-6.0% of Cu, 0.5%-1.0% of Mn, 0.6%-1.0% of Si and the balance Fe is adopted and formed by mixing the chemical components; and then, cladding technological parameters of which the power is 400-500 W, the powder feeding rate is 3.0%-4.0% g / min, the spot diameter is phi 1.0%-1.2 mm, the nozzle scanning speed is 8.0%-10.0% mm, the lapping rate is 50% and the level height is 0.5 mm are adopted, and laser cladding repair is conducted on the abrasive surface of the inner wall of the turbine bearing seat through coaxial powder feeding nozzles.

Description

technical field [0001] The invention relates to the field of maintenance of aero-engine components, and is mainly applied to a method for repairing the abrasion of the inner wall of a rear bearing seat of an aero-engine turbine. technical background [0002] The turbine bearing seat is an important component for the air engine to withstand the axial force of the rotor backward, and it is a ball bearing cast from martensitic stainless steel 1Cr17Ni2. The contact angle of the ball bearing is large, the cage protrudes from the end face of the ring and has an oil retaining edge, and an oil groove or oil hole is opened on the inner diameter to facilitate the circulation of lubricating oil. If the lubricating oil stays in the bearing cavity for too long, it will cause the bearing cavity to overheat; if it stays for a short time, it may cause insufficient lubrication, forming a certain oil flow defect area, resulting in "idling" phenomenon, which will aggravate the bearing wear an...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/10C22C38/42C22C38/02C22C38/04
CPCC23C24/103C22C38/02C22C38/04C22C38/42
Inventor 郭双全窦磊谢佳俊何勇张铀
Owner PLA NO 5719 FACTORY
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