Process for repairing turbine components
AssigneeGeneral Electric Company
InventorsPazhayannur Ramanathan Subramanian, James Anthony Ruud, Laurent Cretegny
Life of this patent
Estimating the term…
Abstract
A process for repairing a turbine component comprises overlaying a preform of a brazing material onto a surface of the turbine component, wherein the surface comprises a damaged portion; securing the preform of a brazing material to the surface; and heating the turbine component to a temperature effective to form a brazed joint between the brazing material and the turbine component. Also disclosed is a repaired turbine component repaired by the process.
Claims16
A process for repairing a turbine component, comprising:
- removing a damaged portion from a surface of the turbine component to form a recessed portion in the surface;
- overlaying a preform consisting of brazing material onto the recessed portion;
- securing the preform;
- and
- heating the turbine component to a temperature effective to form a brazed joint between the brazing material and the turbine component, wherein heating the turbine component comprises stepwise heating to a temperature greater than a melting temperature of the brazing material and less than a melting temperature of the turbine component.
A process for repairing a turbine component, comprising:
- removing a damaged portion from a surface of the turbine component to form a recessed portion in the surface;
- overlaying a preform consisting of brazing material onto the recessed portion;
- securing the preform to the surface, wherein securing the preform to the surface comprises spot welding;
- and
- heating the turbine component to a temperature effective to form a brazed joint between the brazing material and the turbine component.
A process for repairing a turbine component, comprising:
- removing a damaged portion from a surface of the turbine component to form a recessed portion in the surface;
- spot welding at least one preform consisting of a brazing material to the recessed portion, wherein the preform has lateral dimensions about equal to lateral dimensions of the recessed portion;
- and
- heating the turbine component to a temperature sufficient to form a brazed joint between the brazing material and the turbine component.
Dependencies are inferred from the claim text.