Patent ID: 7220326

Claim:
Second and third stage nozzles installed in second and third turbine stages, respectively, of a gas turbine engine, the second turbine stage having a thermal environment that is more severe than the third turbine stage, the second and third stage nozzles being cast from first and second nickel-base alloys, respectively, each consisting of cobalt and, approximately by weight, 22.2% to 22.8% chromium, 1.8% to 2.2% tungsten, 1.2% to 2.3% aluminum, 1.6% to 2.4% titanium, the sum of aluminum and titanium being 2.8% to 4.4%, 0.7% to 0.9% columbium, 0.9% to 1.9% tantalum, 0.003% to 0.009% boron, 0.002% to 0.02% zirconium, 0.05% to 0.10% carbon, with the balance essentially nickel and incidental impurities; wherein the first and second alloys only differ by having cobalt contents of, by weight, 18% to 20% and 5% to 8%, respectively.