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A kind of repairing material and repairing method for repairing turbine blade tip crack

A technology of turbine blade and repair method, which is applied in the coating process and coating of metal materials, can solve the problems of easy precipitation of the second phase, micro cracks, large heat-affected zone, etc., and achieve the effect of promoting application development

Active Publication Date: 2019-11-05
成都天翔动力技术研究院有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

DZ125 is a high-temperature alloy of high aluminum and titanium (the weight percentage of Al+Ti is about 8%), and the blade is made of directional solidification crystal precision casting. Conventional methods such as argon arc surfacing welding are easy to repair deep cracks in the blade tip. New cracks are generated along the direction of directional solidification crystallization, which is mainly due to the non-concentration of conventional argon arc welding energy, large heat-affected zone, and high aluminum and titanium content make the second phase easy to precipitate during welding, which leads to the thermal expansion coefficient of the matrix microcracks
At present, there is no public report in China about the repair method of deep cracks in the working blade tip of directional solidification high-pressure turbine

Method used

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  • A kind of repairing material and repairing method for repairing turbine blade tip crack
  • A kind of repairing material and repairing method for repairing turbine blade tip crack
  • A kind of repairing material and repairing method for repairing turbine blade tip crack

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Effect test

Embodiment 1

[0032] A repairing material for repairing cracks at the tip of turbine blades, which is a high-strength oxidation-resistant nickel-based superalloy powder, consisting of the following components in mass percentage: 8.6% chromium, 15% cobalt, 0.25% carbon, and 2.3% molybdenum , 3.4% tungsten, 6.1% aluminum, 5.4% tantalum, 0.03% zirconium, 0.05% boron, 1.6% rhenium, 1.5% hafnium, and the balance is nickel.

Embodiment 2

[0034] A repairing material for repairing cracks at the tip of turbine blades, which is a high-strength oxidation-resistant nickel-based superalloy powder, composed of the following components in mass percentage: 10% chromium, 13% cobalt, 0.2% carbon, and 2.7% molybdenum , tungsten 4.1%, aluminum 6%, tantalum 6.2%, zirconium 0.05%, boron 0.02%, rhenium 2%, hafnium 2.7%, and the balance is nickel.

Embodiment 3

[0036] A repairing material for repairing cracks at the tip of turbine blades, which is a high-strength anti-oxidation nickel-based superalloy powder with a particle size of -100~+325 mesh, composed of the following components in mass percentage: 9% chromium, cobalt 14%, carbon 0.22%, molybdenum 2.5%, tungsten 4%, aluminum 6.2%, tantalum 6%, zirconium 0.04%, boron 0.03%, rhenium 1.8%, hafnium 2%, and the balance is nickel.

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Abstract

The invention relates to the technical field of maintenance of aviation engines, in particular to a repair material for repairing turbine blade tip cracks and a repair method thereof. The repair material is high-strength oxidation resisting nickel base high-temperature alloy powder; an inert atmosphere induction preheating laser cladding technology is adopted to repair deep crack parts at blade tips of high-pressure turbine working blades; the high-pressure turbine working blades adopt the materials of directional solidification nickel base high-temperature alloys DZ125; and the repair process comprises coating layer removal-polishing of blade tip deep cracks-repair path planning-inert atmosphere induction preheating-laser cladding-shape finishing by manual polishing-coating layer recovery. The repair material realizes repair of directional solidification high-pressure turbine working blades with cracks extending to a cover plate; the cracks are not discovered by the X-ray and fluorescent penetrant inspection after repair; a repair interface has an oriented crystal structure; the life of the repaired high-pressure turbine working blades can reach above 380 hours; and the repair material has important significance on acceleration of application and development of the aviation technology.

Description

technical field [0001] The invention relates to the technical field of aero-engine maintenance, in particular to a repairing material and a repairing method for repairing cracks at the tips of turbine blades. Background technique [0002] The working blade of a certain type of aero-engine high-pressure turbine is made of nickel-based superalloy DZ125 directionally solidified crystal precision casting. After a period of overhaul, a large number of longitudinal cracks appear on the blade tip of the high-pressure turbine blade during operation. Research shows that the deep cracks on the blade tip of the high-pressure turbine blade are mainly thermal fatigue cracks. Most of the cracks have cracked to the cover plate. crack category. DZ125 is a high-temperature alloy of high aluminum and titanium (the weight percentage of Al+Ti is about 8%), and the blade is made of directional solidification crystal precision casting. Conventional methods such as argon arc surfacing welding are...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C24/10C22C19/05
CPCC22C19/057C23C24/103
Inventor 郭双全刘瑞何勇张铀罗奎林
Owner 成都天翔动力技术研究院有限公司
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