Braze repair of turbomachine engine component

Abstract

System (10) and methods (1000) for structural braze repair of high gamma prime nickel base gas turbine components (1). The system may include a controller (200) operably connected to a heating system (100), e.g., a vacuum furnace, for controlling heat temperatures of the furnace for a specified or predetermined time period. A damaged component is placed in the furnace and heated to a first temperature, which is held for the specified time period before being cooled to about room temperature. The component is then heated to a second temperature higher than the first temperature, which is held for a second time period before being cooled again to about room temperature. After cooling the component may be braze repaired at a third temperature equal to or higher than the previous temperatures for a third time period.

Dependencies are inferred from the claim text.