System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip

A technology for turbine blades and high-temperature alloys, which is applied in the system field of repairing nickel-based single-crystal superalloy turbine blade tips, and can solve problems such as difficult to meet the repair requirements of single-crystal blades, cracks easily appear at grain boundaries, and affect blade performance.

Inactive Publication Date: 2016-06-22
SHANGHAI JIAO TONG UNIV
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

Once the grain boundary appears, cracks are likely to appear at the grain boundary and extend along the grain boundary under high thermal st

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  • System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip
  • System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip
  • System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip

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[0024] The specific embodiments of the present invention are given below in conjunction with the drawings, but the present invention is not limited to the following embodiments. According to the following description and claims, the advantages and features of the present invention will be clearer. It should be noted that the drawings all adopt a very simplified form and all use imprecise ratios, which are only used for the purpose of conveniently and clearly assisting in describing the embodiments of the present invention.

[0025] Please refer to figure 1 , figure 1 Shown is a schematic structural diagram of a coaxial powder feeding laser cladding head according to a preferred embodiment of the present invention. The present invention provides a system for repairing the tip of a nickel-based single crystal superalloy turbine blade, which includes a laser, a powder feeder, a mechanical arm, a controller, a positioner and a coaxial powder feeding cladding head, wherein the single ...

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Abstract

The invention provides a system and method for repairing a nickel-based monocrystal high-temperature alloy turbine blade tip. The system comprises a laser device, a powder feeder, a mechanical arm, a controller, a positioner and a coaxial powder feeding cladding head. The method comprises the steps that a monocrystal turbine blade to be repaired is ground, cleaned and fixed to the positioner through a clamp, the laser device and the powder feeder are connected to the coaxial powder feeding cladding head, the coaxial powder feeding cladding head is fixed to the mechanical arm and is perpendicular to the surface of the monocrystal turbine blade tip, and the controller controls the motion path of the mechanical arm. By the adoption of the system and method for repairing the nickel-based monocrystal high-temperature alloy turbine blade tip, the monocrystal turbine blade tip can be successfully repaired through net shaping, the interior of the repaired monocrystal blade tip is compact and continuous monocrystal structures, and the using requirements of the monocrystal blade can be completely met through subsequent machining.

Description

technical field [0001] The invention relates to the field of laser repair and material microstructure growth, and in particular to a system and method for repairing the tip of a nickel-based single crystal superalloy turbine blade. Background technique [0002] With the increasing working temperature of modern aero-engines, nickel-based single crystal superalloys have been widely used to manufacture high-temperature turbine blades. Nickel-based single crystal alloy turbine blades are expensive, with a unit price of up to 30,000 US dollars per piece. Due to the harsh working environment of aero-engines, defects such as wear, corrosion, cracks, and material loss are prone to occur at the blade tip. Prolonging the service life of single crystal turbine blades through repair technology can reduce aeroengine maintenance costs, save expensive materials, and generate huge economic benefits. The repair process steps mainly include: blade cleaning, blade tip inspection, crack clean...

Claims

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Application Information

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IPC IPC(8): C23C24/10
CPCC23C24/106
Inventor 刘朝阳顾剑锋
Owner SHANGHAI JIAO TONG UNIV
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