Patent ID: 7882639

Claim:
A gas turbine engine stationary shroud repaired according to the method comprising the steps of: providing the gas turbine engine stationary shroud having an undersize repair region made of a shroud material, wherein the repair region is a protruding element located on a gas flow path surface of the gas turbine engine stationary shroud; repairing the repair region of the gas turbine engine stationary shroud so that the repair region is no longer undersize, further including the steps of: removing the protruding element from the shroud; forming a receiving groove in the repair region, the groove extending below the gas flow path surface; placing a replacement element into the receiving groove; placing a braze repair material in the repair region, the braze repair material having a solidus temperature less than that of the shroud material; heating the repair region, the replacement element, and the repair material to a brazing temperature sufficient to melt at least a portion of the braze repair material but not the replacement element or shroud material of the repair region, so that the repair material flows over the repair region, into the groove, contacting the replacement element and the gas flow surface; and thereafter cooling the melted braze repair material and the repair region to solidify the braze repair material; wherein the step of placing a repair material in the repair region includes placing the repair material in the receiving groove.