Patent ID: 8156649
Filing Date: 2012-04-17
Classification: B23K,B23P,F01D,F05D,Y10T

Abstract:
1. A gas turbine engine hot gas component repair method for defects that do not extend through a thickness of the component, comprising: a) machining at least one cavity in a surface of the component to remove at least one defect from the component; b) manufacturing at least one coupon fittable within the cavity; c) applying a brazing medium to the coupon to enable brazing of the coupon to the component; d) fitting the coupon as a fitted coupon into the cavity; e) joining the fitted coupon to the component at an outer edge of the fitted coupon; f) applying foil or sheet brazing medium to the joined coupon to cover the joined coupon and form an outer surface of the component to provide a thickness of the component; and g) subjecting the component to a thermal cycle wherein the foil or sheet brazing medium is brazed to an outer surface of the coupon.