Patent ID: 8555500
Filing Date: 2013-10-15
Classification: B23K,B23P,F01D,F05D,Y10T

Abstract:
1. A method of producing or repairing single-crystalline turbine or engine components by means of the following steps: heating of braze filler metal at a constant temperature rate to a peak temperature of 1200 to 1260° C., which is greater than or equal to the melting temperature of the braze filler metal; maintaining the braze filler metal at the peak temperature for 15 to 45 minutes; introducing a molten mass of the braze filler metal produced through the heating process into one of a crack formed in the turbine or engine component, a gap formed between two turbine or engine components, or a damaged area of a turbine or engine component; and non-isothermal control of the temperature of the braze filler metal or turbine or engine component by cooling the braze filler metal at a constant temperature rate during an epitaxic solidification process of said braze filler metal.