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Process for repairing turbine engine components

A component and turbine blade technology, applied in the field of repairing turbine engine components, can solve the problems of molybdenum refractory metal core deformation and waste

Inactive Publication Date: 2008-01-23
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, the molybdenum refractory metal core becomes deformed (see area 10) and results in a scrap situation

Method used

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  • Process for repairing turbine engine components
  • Process for repairing turbine engine components

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Embodiment Construction

[0012] According to the present invention, there is provided a method for repairing a turbine engine component, such as a turbine blade or airfoil, formed from a superalloy material, such as a nickel- or cobalt-based alloy, and used in a gas turbine engine. The method broadly includes placing a component of refractory metallic material over the area of ​​the component to be repaired and depositing a repair filler metal material adjacent to and around the refractory metallic material in an amount sufficient to fill the space to be repaired and to its soldered. The repair filler metal material balls and flows on the refractory metal material. The continuous beading of the repair filler metal material (ie repeated heating via the welding operation) gradually covers the entire refractory metal material, allowing the operator to rebuild the blade or airfoil wall and tip. Throughout the process, the refractory metallic material is not directly exposed to the heat of the continuous ...

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Abstract

A process for repairing a component includes the steps of placing a piece of refractory metal material (16) over an area (12) of component to be repaired; depositing a repair filler metal (18) material proximate to the piece of refractory metal material (16) in an amount sufficient to repair the component; subjecting the repair filler material (18) to a welding treatment without directly heating the piece of refractory metal material (16); flowing the repair filler material (18) within the area (12); and casting the repair filler material (18).

Description

technical field [0001] The present invention relates to a method of repairing turbine engine components, and more particularly, to repairing turbine blades of a turbine engine. Background technique [0002] Today, gas turbine blade tip and trailing edge regions are repaired using welding methods such as gas tungsten arc welding with substrate materials such as refractory metal cores. Welds are used to plug cracks and wear surfaces. However, there is a risk of excessive heat input melting the substrate material. Problems arise when the soldering process heats and melts the substrate material. If the backing material survives this damage, the backing material will alloy with the weld metal, thus making an unacceptable repair. In this case, the substrate material becomes deformed and causes a waste situation. For example, FIG. 1 shows a cross-sectional view of a welded blade tip 2 in which a molybdenum refractory metal core 4 is melted during the welding process and subsequ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00
CPCF01D5/005F05D2230/21F05D2230/232F05B2260/202F05B2230/30B23P6/007F05D2240/122F05D2240/304F05D2260/202B23K2201/001F05D2230/30F05B2230/232F05B2230/21B23K2101/001
Inventor C·瓦加斯W·M·罗斯
Owner UNITED TECH CORP