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Composite powder for high-strength and high-crack-resistance laser additive repair and preparation method thereof

A laser additive and composite powder technology, applied in the field of powder metallurgy, can solve problems such as difficulty in meeting high crack resistance requirements, cracking in the repair area, repair failure, etc., and achieve the effect of reducing impurity content, avoiding plasticity decline, and improving purity

Active Publication Date: 2022-03-11
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because these single powders have the disadvantage of poor plasticity while meeting high strength, it is difficult to meet the high crack resistance requirements, resulting in cracking of the repair area during the repair process or subsequent use, resulting in repair failure

Method used

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  • Composite powder for high-strength and high-crack-resistance laser additive repair and preparation method thereof
  • Composite powder for high-strength and high-crack-resistance laser additive repair and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] First, the spherical powder A powder was prepared by argon atomization method using the master alloy. The weight percentages of the chemical components in the A powder were: carbon was 0.07%, chromium was 22.0%, cobalt was 0.7%, molybdenum was 9.0%, and aluminum was 0.3%, titanium is 0.3%, nickel is the balance; powder particle size is 53-105μm;

[0022] Then use the master alloy to prepare spherical powder B powder by argon atomization method. The weight percentages of the chemical components in the B powder are: carbon is 0.12%, chromium is 6.8%, cobalt is 11.85%, boron is 0.015%, aluminum is 6.15% %, hafnium is 1.50%, tantalum is 6.35%, molybdenum is 1.5%, tungsten is 4.9%, rhenium is 2.8%, nickel is the balance; powder particle size is 53-105μm;

[0023] Finally, A powder and B powder were mechanically stirred and mixed at a weight ratio of 7%:93%, and the mixing time was 24h.

[0024] A certain type of aero-engine turbine blade tip cracks, a single high-strength p...

Embodiment 2

[0026] Spherical powder A powder is prepared by argon atomization method using master alloy. The weight percentage of each chemical component in A powder is: carbon is 0.05%, chromium is 20.0%, cobalt is 0.5%, molybdenum is 8.0%, aluminum is 0.2% , titanium is 0.2%, nickel is the balance; powder particle size is 53-105μm;

[0027] Then use master alloy to prepare spherical powder B powder by argon atomization method, the weight percentage of each chemical composition in B powder is: carbon is 0.10%, chromium is 6.6%, cobalt is 11.45%, boron is 0.01%, aluminum is 5.94% %, hafnium is 1.30%, tantalum is 6.2%, molybdenum is 1.3%, tungsten is 4.7%, rhenium is 2.6%, nickel is the balance; powder particle size is 53-105μm;

[0028] Finally, A powder and B powder were mechanically stirred and mixed at a weight ratio of 6%:94%, and the mixing time was 24h.

Embodiment 3

[0030] The master alloy is used to prepare A powder by argon atomization method. The weight percentage of each chemical component in A powder is: carbon is 0.1%, chromium is 23.0%, cobalt is 1.0%, molybdenum is 10.0%, and aluminum is 0.4%. , titanium is 0.4%, nickel is the balance; powder particle size is 53-105μm;

[0031] Then use the master alloy to prepare B powder by argon atomization method. The weight percentage of each chemical component in B powder is: carbon is 0.14%, chromium is 7.0%, cobalt is 12.05%, boron is 0.02%, aluminum is 6.30% %, hafnium is 1.70%, tantalum is 6.5%, molybdenum is 1.7%, tungsten is 5.1%, rhenium is 3.0%, nickel is the balance; powder particle size is 53-105μm;

[0032] Finally, A powder and B powder were mechanically stirred and mixed at a weight ratio of 8%:92%, and the mixing time was 24h.

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Abstract

The invention discloses a preparation method of a high-strength and high-crack-resistance composite powder for laser additive repair, which belongs to the field of powder metallurgy and includes the following steps: (1) preparing a spherical powder A powder by an atomization method, and the composition of each chemical component in the A powder The weight percentages are: carbon 0.05-0.1%, chromium 20.0-23.0%, cobalt 0.5-1.0%, molybdenum 8.0-10.0%, aluminum 0.2-0.4%, titanium 0.2-0.4%, and the balance is nickel; (2) using The atomization method prepares the spherical powder B powder, and the weight percentages of each chemical composition in the B powder are: carbon 0.10-0.14%, chromium 6.6-7.0%, cobalt 11.45-12.05%, boron 0.01-0.02%, aluminum 5.94-6.30%, Hafnium 1.30-1.70%, tantalum 6.2-6.5%, molybdenum 1.3-1.7%, tungsten 4.7-5.1%, rhenium 2.6-3.0%, and the balance is nickel; (3) A powder and B powder are mixed in a weight ratio of 8-6 %: 92-94% for stirring and mixing, the mixing time is not less than 24h. The invention is used for repairing the cold end and the hot end parts of the aero-engine, which not only ensures the strength of the whole repair area, but also solves the difficult problem of cracking in the repair area.

Description

technical field [0001] The invention belongs to the field of powder metallurgy, and in particular relates to a composite powder for high-strength and high-crack resistance laser additive repair and a preparation method thereof. Background technique [0002] Laser additive repair technology is often used in aero-engines to repair various cold-end and hot-end parts. In order to meet the requirements of high-temperature strength and anti-oxidation service environment, the existing technology usually uses high-strength superalloy powder in the repair process of hot-end parts. (In 738, Rene142, Rene125, Rene 80) Repair wear or cracks. Because these single powders have the disadvantage of poor plasticity while meeting high strength, it is difficult to meet the high crack resistance requirements, which will lead to cracking of the repaired area during the repair process or subsequent use, resulting in repair failure. Contents of the invention [0003] Aiming at the above technic...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22F9/08B22F10/28B33Y70/00C22C19/05B22F7/06C23C24/10
CPCB22F9/082C22C19/055C22C19/058B33Y70/00B22F7/062B22F2007/068B22F10/00B22F10/36B22F10/34B22F10/20Y02P10/25
Inventor 张铀郭双全滕江刘瑞罗九龙罗奎林张凯何勇杨秀恩
Owner PLA NO 5719 FACTORY
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