Method for repairing wear of inner wall of intermediate casing of engine

A wear repair and engine technology, applied in the direction of coating, metal material coating process, etc., to achieve the effect of satisfying the performance

Inactive Publication Date: 2013-03-06
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] There are two problems to be solved for the wear and fusion welding repair of the inner side of the intermediate casing drum. One is to ensure that the casing does not deform after welding, even if the benchmark of the axial concentricity of the engine remains unchanged. no peeling

Method used

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  • Method for repairing wear of inner wall of intermediate casing of engine
  • Method for repairing wear of inner wall of intermediate casing of engine
  • Method for repairing wear of inner wall of intermediate casing of engine

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Embodiment

[0018] The material of the intermediate casing is BT20 titanium alloy, and its chemical composition is shown in Table 1. This alloy is a near-α-type titanium alloy with high Al equivalent, the strength level exceeds 930MPa, and the working temperature can reach 500°C. Up to 800°C, and when working at 450°C, the life span can reach 6000h.

[0019] Table 1 Chemical composition of BT20 titanium alloy (wt%)

[0020] Al

Zr

Mo

V

Ti

5.5～7.5

1.5～2.5

0.5～2.0

0.8～1.8

the remaining

[0021] Specific process steps:

[0022] 1) Fault inspection: carry out fault inspection on the intermediate casing, and measure the wear depth (generally, the depth is 0.04-0.1, and 10 places are evenly distributed along the circumference).

[0023] 2) Cleaning before welding: polish the worn parts with emery cloth.

[0024] 3) Make the welding test piece: measure the size of the worn part, select the welding test piece with a thickness of 0.2mm, and...

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Abstract

The invention aims to provide a method for repairing the wear of the inner wall of an intermediate casing of an engine, and the method is characterized in that a laser cladding method is adopted to repair the worn part on the inner wall of the intermediate casing of the engine; the repair process is as follows: a cladding material is a BT20 titanium alloy; the weight percentage of the components of the titanium alloy is as follows: 5.5 percent to 7.5 percent of aluminum (Al), 1.5 percent to 2.5 percent of zirconium (Zr), 0.5 percent to 2.0 percent of molybdenum (Mo), 0.8 percent to 1.8 percent of vanadium (V), and the rest titanium (Ti); the single-pulse energy is 50J, the frequency is 4Hz, the pulse width is 5ms, the focus is 150mm, the diameter of light spots is 1.2mm, the scanning speed is 1.2mm / s and argon is adopted for protection. Due to the adoption of the method, the service life of the intermediate casing in the aero-engine can be prolonged, so that the intermediate casing can work in a complete technical state, and the use performance is met.

Description

technical field [0001] The invention relates to the field of engine repair, and in particular provides a method for repairing the inner wall wear of an engine intermediate case. Background technique [0002] The engine intermediate casing is an important load-bearing component connecting the high and low pressure compressor rotors of the engine, and is the benchmark of the axial concentricity of the engine. It has a large clearance fit with the elastic ring. During the working process of the intermediary casing, its The inner wall will be worn out by the boss of the matching elastic ring (the area is about 45×5), and the wear depth cannot be greater than 0.04, but many actual parts wear more than 0.04 depth. At present, the wear and tear of the intermediate casing is mainly used to assemble the elastic ring by transposition, so as to avoid the worn area, so that the intermediate casing can be used again. However, with this method, the intermediate casing works under the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/10C22C14/00
Inventor 李丹赵四洋张革王茅才谢玉江
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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