Patent ID: 8544716
Filing Date: 2013-10-01
Classification: B23K,B23P,C22C,F01D,F05D,Y10T

Abstract:
1. A method for repairing a component of a gas turbine, comprising the steps of: applying a solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, wherein the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder; applying a molded repair part made of the solder alloy to the component in an area of the component having a planar defect; heat treating the component to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection; cooling the component after the heat treating; and following the cooling, further heat treating the component wherein the further heat treating includes three sequences of a cooling and a heating.