A monocrystalline superalloy with a nickel based matrix and particularly intended for the manufacture of turbine blades, has the following composition, by weight: Al=5.4% to 6.2%; Co=4% to 7%; Cr=6% to 9%; Mo=0% to 2.5%; Ta=5.5% to 8%; Ti=0% to 1%; Wt32 7% to 9%; and Ni=balance to 100%. The invention also provides a method of improving the alloy\'s resistance to creep, in which the Ni.sub.3 Al type .gamma.\' phase is put completely into solution at a first temperature, and then the .gamma.\' phase is precipitated into the .gamma. solid solution at a temperature greater than 1000.degree. C. This treatment considerably increases the alloy\'s resistance to creep over a wide range of temperatures.

Claims

17 · 3 independent · depth 3

17 granted claims

›1.independentA monocrystalline super alloy with a nickel based matrix having a gamma-prime phase with a grain size of 5000 .ANG. algined along a well defined cryst…+3

›5.independentA method of producing a single crystal superalloy part suited for use as a blade in an aeroengine turbine which comprises the steps of: (a) forming an…+7

›6.↳ 5The method defined in claim 5, step (d), wherein the alloy part is maintained at said temperature for several hours.d2

›7.↳ 5The method defined in claim 5, further comprising the step of: (e) following step (d), subjecting the alloy part to cooling in the air to ambient temp…d2+1

›9.↳ 5Th method defined in claim 5, wherein a surface protection treatment is applied to the alloy part while it is being maintained at the temperature for …d2

›10.↳ 5The method defined in claim 5 wherein the alloy consists essentially of: ______________________________________ Al 5.5% Co 5% Cr 8% Mo 0.5% Ta 6% Ti 1…d2+1

›11.↳ 5The superalloy part suited for use as a blade in an aeroengine turbine made by the method defined in claim 5.d2

›13.independentA method of producing a single crystal superalloy suited for ue as a blade in an aeroengine turbine which comprises the steps of: (a) forming an alloy…+4

Classifications

5 codes

USPC · US Patent Classification

148/3148/13.1148/410148/404148/162

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R. Dean

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