Gas turbine hot gas component repair method

摘要

A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component (10). Coupons (20), fittable within the cavities are manufactured, coated with brazing medium (25) on an inner surface and then joined to the component, by joining means such as laser metal forming. The joint holds the coupon during later heat treatment eliminating the need for holding aids. Before heat treatment further brazing medium (29) is applied to the surface of the coupon (20) overlapping onto the component (10). A single heat treatment, brazing the coupon (20) to the component (10), brazing the brazing medium (29) to the outer surface of the coupon (20), then completes the repair.