Patent ID: 6464128
Filing Date: 2002-10-15
Classification: B23K,B23P,F01D,F05D,Y02T,Y10T

Abstract:
A method of repairing a gas turbine engine stationary shroud, comprising the steps ofproviding the gas turbine engine stationary shroud having an undersize repair region made of a shroud material, wherein the repair region is not 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, the step of repairing including the steps of providing a sufficient mass of a repair material comprising a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component, wherein the first alloy component and the second alloy component have different solidus temperatures, placing the repair material into the repair region, heating the repair material and the repair region to a brazing temperature sufficient to melt at least a portion of the repair material but not the shroud material of the repair region, so that the repair material flows over the repair region, and thereafter cooling the melted repair material and the repair region to solidify the repair material, the repair material having a solidus temperature less than that of the shroud material.