Repair material and repair method for directional solidification crystal turbine blade tip deep cracks

A turbine blade and directional solidification technology, which is applied in the direction of turbines, additive processing, mechanical equipment, etc., can solve problems such as micro-cracks and repair failures, shorten the maintenance cycle, enhance weldability, and ensure repair quality.

Active Publication Date: 2021-03-02
PLA NO 5719 FACTORY
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  • Abstract
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Problems solved by technology

[0004] The present invention firstly provides a material for repairing deep cracks in the directionally solidified crystal turbine blade tip, which solves the problem of easy micro-cracks in existing repair materials, resulting in repair failure The problem

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  • Repair material and repair method for directional solidification crystal turbine blade tip deep cracks
  • Repair material and repair method for directional solidification crystal turbine blade tip deep cracks

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Embodiment Construction

[0024] The present invention will be further described below in conjunction with embodiment.

[0025] The first subject of the present invention is: the repair material for directionally solidified crystal turbine blade tip deep cracks, which is formed by fully mixing 35% to 45% of Inconel625 alloy powder and 55% to 65% of Rene142 alloy powder by mass . The percentage of Inconel625 alloy powder can be any integer between 35 and 45, for example: the mass ratio of Inconel625 alloy powder to Rene142 alloy powder is 40:60. The restorative material is made by mixing two alloy powders, which are physically mixed, and the two alloy powders are existing. In order to ensure the uniformity of the two alloy powders after mixing, the Inconel625 alloy powder and the Rene142 alloy powder are mixed in proportion, and mechanically stirred for at least 24 hours to make the mixture uniform.

[0026] The second subject of the present invention is: the repair method of directionally solidified ...

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Abstract

The invention discloses a repair material and a repair method for directional solidification crystal turbine blade tip deep cracks, relates to the field of aero-engine blade maintenance, and solves the problem that existing repair materials are likely to generate micro-cracks. According to the technical scheme, the repair material for the directional solidification crystal turbine blade tip deep cracks is formed by fully mixing 35%-45% of Inconel 625 alloy powder and 55%-65% of Rene 142 alloy powder by mass. The repair method for the directional solidification crystal turbine blade tip deep cracks comprises the steps that after a high-pressure turbine working blade is decomposed, flaw detection is conducted firstly, the crack position is determined, and a groove is formed; then, the aboverepairing material is adopted for laser additive manufacturing; a repair area is polished, and the blade is placed in a vacuum furnace for annealing treatment; and finally, flaw detection is conductedon the blade. The repair material and the repair method are suitable for repairing the deep cracks of the blade tip of the directional solidification nickel-based superalloy DZ125 turbine rotor blade.

Description

technical field [0001] The invention relates to the technical field of maintenance of aeroengine blades, in particular to a method for repairing deep cracks on the tip of a directionally solidified nickel-based superalloy DZ125 turbine rotor blade. Background technique [0002] The working blades of the high-pressure turbine of a certain type of domestic aero-engine are made of nickel-based superalloy DZ125 directional solidification crystal precision casting, and the cover plate of the high-pressure turbine working blade is brazed to the blade body. The failure inspection of the working blades of this type of high-pressure turbine after disassembly showed that more than 70% of the blades were scrapped due to deep cracks at the tip of the blade (the longest crack was 4mm, extending to the cover plate and below the cover plate), and the scrap rate of some units reached 100%. Due to the complex casting process of high-pressure turbine working blades, high machining accuracy re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F1/00B22F7/06B22F10/28B22F10/64B22F5/04B33Y70/00B33Y10/00B33Y40/20
CPCB22F1/0003B22F7/062B22F5/04B33Y70/00B33Y10/00B33Y40/20B22F2007/068Y02P10/25
Inventor 刘瑞陈海生郭双全胡兵罗九龙段俊菲罗光荣
Owner PLA NO 5719 FACTORY
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