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Local size repairing method for engine titanium alloy component

A repair method and technology of titanium alloy, applied in metal material coating process, liquid chemical plating, coating and other directions, can solve the problems of easy adhesion, high cost, easy surface scratches, etc., to improve wear resistance and Surface hardness, significant economic and social benefits, effect in meeting production and repair requirements

Inactive Publication Date: 2018-06-01
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Titanium alloy has many excellent properties, such as high corrosion resistance and high temperature resistance, and is an indispensable material in the aerospace chemical and petroleum industries. However, the alloy has some defects, such as poor wear resistance and easy scratches on the surface. Mutual adhesion is easy to occur. After the engine is in service, due to the relative movement and wear between the parts and the corrosion of the service environment, scratches and wear often occur on the surface of the parts during the overhaul. After mechanical grinding and trimming, the size exceeds the requirements of the design drawings. Affect normal installation and use
Conventional methods such as surfacing and replacement are not only long-term, but also costly

Method used

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  • Local size repairing method for engine titanium alloy component
  • Local size repairing method for engine titanium alloy component
  • Local size repairing method for engine titanium alloy component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] The process flow is: degreasing→non-plating surface protection→sand blasting→corrosion→activation treatment→pre-nickel plating→electroless nickel plating→heat treatment; among them:

[0034] The degreasing process is to chemically degrease the parts in an organic solvent and an alkaline salt solution in sequence. The composition and content of the alkaline salt solution are:

[0035]

[0036] Activation treatment:

[0037] Activation bath composition and content:

[0038]

[0039] The preparation of the activation treatment solution is to slowly add sulfuric acid to hydrochloric acid under constant stirring and cooling (the following examples all adopt this method). The color of the part after activation treatment is gray, and there is a small amount of sediment on the part.

[0040] Nickel pre-plated:

[0041] Contact nickel plating bath composition and content:

[0042]

[0043] After treatment, a layer of copper is uniformly deposited on the surface of t...

Embodiment 2

[0051] Activation treatment:

[0052] Activation bath composition and content:

[0053]

[0054] The color of the parts after activation treatment is gray, and there is no sediment on the parts. Nickel pre-plated:

[0055] Contact nickel plating bath composition and content:

[0056]

[0057] After treatment, a layer of copper is uniformly deposited on the surface of the part.

[0058] Electroless Nickel:

[0059] Chemical nickel plating bath composition and content:

[0060]

[0061]

[0062] Temperature: 90°C

[0063]

[0064] The coating prepared by the above process was heated at 250°C for 1 hour without foaming, and the microhardness of the coating was HV650. After being treated at 350°C for 1 hour, the microhardness was greater than HV850, and the deposition rate was 15 μm / h.

Embodiment 3

[0066] Activation treatment:

[0067] Activation bath composition and content:

[0068]

[0069] The color of the part after activation treatment is gray, and there is a small amount of sediment on the part.

[0070] Nickel pre-plated:

[0071] Contact nickel plating bath composition and content:

[0072]

[0073]

[0074] After treatment, a layer of copper is uniformly deposited on the surface of the part.

[0075] Electroless Nickel:

[0076] Chemical nickel plating bath composition and content:

[0077]

[0078] Temperature: 88°C

[0079]

[0080] The coating prepared by the above process was heated at 250°C for 1 hour without foaming, and the microhardness of the coating was HV590. After being treated at 350°C for 1 hour, the microhardness was greater than HV800, and the deposition rate was 13 μm / h.

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Abstract

The invention aims at providing a local size repairing method for an engine titanium alloy component. The local size repairing method is characterized in that a chemical nickel plating method is adopted for size repairing; and the technology process is oil removal, non-plated surface protection, sand blowing, corroding, activating treatment, nickel preplating, chemical nickel plating and heat treatment. The method can solve the problems about component size out-of-tolerance and old clad layer repairing, the service life of components is prolonged, the engine producing and repairing requirements are met, the repairing cost is reduced, and obvious economic and social benefits are achieved.

Description

technical field [0001] The invention relates to a method for repairing the size of titanium alloy parts of an aero-engine, in particular to a process method for electroless nickel plating of titanium alloys. Background technique [0002] Titanium alloy has many excellent properties, such as high corrosion resistance and high temperature resistance, and is an indispensable material in the aerospace chemical and petroleum industries. However, the alloy has some defects, such as poor wear resistance and easy scratches on the surface. Mutual adhesion is easy to occur. After the engine is in service, due to the relative movement and wear between the parts and the corrosion of the service environment, scratches and wear often occur on the surface of the parts during the overhaul. After mechanical grinding and trimming, the size exceeds the requirements of the design drawings. Affect the normal installation and use. Conventional methods such as surfacing welding and parts replacem...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C18/36C23G1/20C23C18/18C23C18/54B23P6/00
CPCC23C18/36B23P6/00C23C18/1889C23C18/54C23G1/205
Inventor 王辉滕志强杨树林杜兴盛张颖
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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