Patent ID: 7506793

Claim:
A method of repairing a turbine component of a gas turbine, the method comprising the steps of: mixing powders of a cobalt-base braze alloy and a cobalt-base wear-resistant alloy to form a powder mixture, the cobalt-base braze alloy constituting about 10 to about 35 weight percent of the powder mixture and containing a sufficient amount of boron so that the cobalt-base braze alloy has a melting temperature of about 1090° C. to about 1230° C., wherein the cobalt-base braze alloy consists of, by weight, about 22.00 to about 24.75% chromium, about 9.0 to about 11.0% nickel, about 6.5 to about 7.6% tungsten, about 3.0 to 4.0% tantalum, about 2.60 to 3.16% boron, about 0.55 to about 0.65% carbon, about 0.15 to 0.30% titanium, about 0.30 to 0.60% zirconium, up to 1.3% iron, up to 0.4% silicon, up to 0.10% manganese, up to 0.015% sulfur, and the balance cobalt and incidental impurities, and wherein the cobalt-base wear-resistant alloy consists of, by weight, about 26.0 to about 30.0% chromium, about 18.0 to about 21.0% tungsten, about 4.0 to about 6.0% nickel, about 0.75 to about 1.25% vanadium, about 0.7 to about 1.0% carbon, up to 3.0% iron, up to 1.0% manganese, up to 0.5% molybdenum, up to 1.0% silicon, up to 0.05% boron, and the balance cobalt and incidental impurities; sintering the powder mixture to form a sintered preform; removing a surface portion of the turbine component to expose a subsurface portion of the turbine component; and then diffusion bonding the sintered preform to the subsurface portion of the turbine component to form a wear-resistant repair material consisting of the cobalt-base braze alloy dispersed in a matrix of the wear-resistant cobalt-base alloy.