Turbine blade superalloy I

Claim 1

An alloy body especially useful in hot stages of industrial gas turbines having improved resistance to long term stress at temperatures in the range 800° to 1100° C. combined with enhanced oxidation and corrosion resistance comprising, in at least part, an aggregation of elongated, essentially parallel metallic crystals having grain boundaries therebetween wherein the average grain aspect ratio of said metallic crystals is at least about 7, said metallic crystals (1) having a γ' phase dispersed therein at a temperature lower than about 1170° C. and (2) having dispersed therethrough particles in the range of about 5 to 500 nanometers in major dimension of a stable yttrium-containing oxidic phase, said metallic crystals and grain boundary material consisting essentially in weight percent of about 18 to about 24% chromium, about 2 to about 6% aluminum, about 2 to about 4% titanium, about 1.5 to about 3.5% tantalum, 0 to about 1% niobium, about 1 to about 3% molybdenum, about 3 to about 6.5% tungsten, up to about 10% cobalt, up to about 2% hafnium, about 0.4 to about 1% oxygen, about 0.4 to about 1% yttrium, up to about 0.2% carbon, up to about 0.05% boron, up to about 0.5% zirconium, up to about 2% iron, up to about 0.5% nitrogen, up to about 4% rhenium in replacement of an equal weight of tungsten or molybdenum, the balance, except for impurities, being essentially nickel, said alloy body having been produced from mechanically alloyed powder.