Method for repairing damage of blade leading edge of TC4 titanium alloy integral bladed-disk structure

A technology for overall blisk and damage repair, applied in the direction of climate sustainability, high-efficiency propulsion technology, metal material coating technology, etc., can solve problems such as easy deformation and collapse, narrow passage, large bending and torsion, etc., to reduce heat Influence and reduce the effect of heat input

Active Publication Date: 2020-11-24
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The overall blisk structure design is complex, with narrow channels, thin blades, and large bending and twisting, which are prone to deformation and collapse during the repair process

Method used

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  • Method for repairing damage of blade leading edge of TC4 titanium alloy integral bladed-disk structure
  • Method for repairing damage of blade leading edge of TC4 titanium alloy integral bladed-disk structure

Examples

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Embodiment

[0030] The air intake side of the overall blisk of a certain type of aero-engine compressor is damaged, and the repair method of the present invention is used to repair it. The steps are as follows:

[0031] S1. Mark the wounded part on the air intake side, measure and determine the depth of the damaged area D = 0.6 mm, and the width of the damaged area H = 1.6 mm.

[0032] S2. Since 3.464D=3.464×0.6=2.0784, so H≤3.464D, the damaged area of ​​the blade is ground into a 120° groove with a depth of 0.6mm and a width of 2.078mm.

[0033] S3. Use TC4 powder to repair the first layer of laser on the groove, the laser power is 240W, the scanning speed is 3mm / s, the focal length is 3, the powder feeding rate is 3g / min, and the repairing path is from P10 to P11 to P12.

[0034] S4. Use TC4 powder to repair the groove with the second laser layer. The laser power is 220W, the scanning speed is 3mm / s, the focal length is 3, and the powder feeding rate is 3g / min. The repairing path is fro...

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Abstract

The invention discloses a laser additive repairing method, relates to the field of maintenance of aero-engines, and aims to provide a method for repairing the damage of a blade leading edge of a TC4 titanium alloy integral bladed-disk structure. According to the technical scheme, the method for repairing the damage of the blade leading edge of the TC4 titanium alloy integral bladed-disk structurecomprises the steps that firstly, the blade leading edge is detected, and a damage area is marked; a V-shaped groove is formed in the damage area, and the damage area is covered with the groove; the groove is subjected to laser additive repair by using TC4 powder along the repair path from one side of the groove to the bottom of the groove to the other side of the groove; the groove is subjected to next-layer repair by adopting the TC4 powder, and the repair laser power is lower than the laser power of the first-layer repair; next-layer repair is repeated until to fill the whole groove; and finally, the profile of the repair area is polished until to meet the size requirements. The method is used for repairing the damage, such as local deformation, scratching, tearing and chipping, of theblade leading edge.

Description

technical field [0001] The invention relates to the field of aero-engine maintenance, in particular to a method for repairing damages such as local deformation, bruising, tearing and block loss of blade inlet edges made of TC4 titanium alloy and integral blisk structure with laser additives. Background technique [0002] The blisk is a key core component that must be used in high thrust-to-weight ratio aeroengines. The use of integral blisks can greatly reduce the number and weight of aeroengine compressor parts, and significantly improve the thrust-to-weight ratio, efficiency and reliability of the engine. The compressor of a certain type of aero-engine adopts an integral blisk structure, and its material is TC4 titanium alloy. The overall blisk is at the front end of the engine, and it is vulnerable to the impact of inhaled foreign objects during service, causing local deformation, damage, tearing or even falling of the blade, resulting in damage to the intake edge of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00C23C24/10
CPCC23C24/103B23P6/007Y02T50/60
Inventor 黄璇璇侯廷红郭双全罗九龙王轶翔程小红
Owner PLA NO 5719 FACTORY
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