Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.

Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.

Abstract: A method is provided for removing a dense ceramic thermal barrier coating (TBC) from an article surface over which the TBC is disposed, the article surface including an edge at which at least a portion of an interface between the article surface and the TBC is exposed. The interface includes at least one material selected from Al, Ti, Cr, Zr and their oxides. The method comprises subjecting at least the exposed interface to a reducing gas at a temperature of at least 1600° F. to separate the TBC from the article surface. The reducing gas is subjected for a time sufficient for the gas to penetrate the interface at least by converting to a gaseous compound at least one material of the group at the interface, and for the TBC to be removed by separation from the article surface.