Patent ID: 6384365
Filing Date: 2002-05-07
Classification: B22F,B23K,B23P,C04B,F01D,F05D,Y02T,Y10T

Abstract:
A method of repairing a combustion turbine component comprising the steps of:(a) providing a worn or damaged turbine component part having at least two approximate opposing surfaces, and a base coat and a thermal barrier coating on the approximate opposing surfaces; (b) removing the base coat and the thermal barrier coating from the approximate opposing surfaces; (c) disposing electrodes in close proximity to the approximate opposing surfaces; (d) generating an electric field to provide heat, and applying additional pressure on the opposing surfaces, resulting in cleaning and short-time high temperature spark plasma sintering between the opposing surfaces within 5 minutes at a temperature up to 1300Â° C.; (e) reducing the electric field; (f) subjecting the two approximate opposing surfaces to additional pressure; and (g) maintaining the pressure while cooling the turbine component approximate opposing surfaces.