Gas turbine blade tip alloy

Details Gas turbine blade tip alloy Gas turbine blade tip alloy

C - Chemistry, Metallurgy

22

C

75/16, 117/230,

C22C 19/05 (2006.01) C22C 30/00 (2006.01)

Patent

CA 1101698

ABSTRACT OF THE DISCLOSURE A nickel base superalloy having a composition which provides a desirable combination of good oxidation and corrosion resistance and hot hardness is described. The alloy contains 21-25% Cr, 4.5-7% Al, 4-10% W, 2.5-7% Ta, 0.5-15% Y and .1-.3% C. This alloy is useful as a blade tip element in a composite gas turbine blade.

301677

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