Ni-Cr-Co alloy for advanced gas turbine engines
OwnerLee Pikeinventor
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Abstract
A wrought age-hardenable nickel-chromium-cobalt based alloy suitable for use in high temperature gas turbine transition ducts possessing a combination of three specific key properties, namely resistance to strain age cracking, good thermal stability, and good creep-rupture strength contains in weight percent 17 to 22 chromium, 8 to 15 cobalt, 4.0 to 9.5 molybdenum, up to 7 tungsten, 1.28 to 1.65 aluminum, 1.50 to 2.30 titanium, up to 0.80 niobium, 0.01 to 0.2 carbon, up to 0.01 boron, and up to 3 iron, with a balance of nickel and impurities. Certain alloying elements must be present in amounts according to two equations here disclosed.
Claims20
A nickel-chromium-cobalt based alloy having a composition comprised in weight percent of:
- 17 to 22 chromium
- 8 to 15 cobalt
- 4.0 to 9.5 molybdenum
- up to 7.0 tungsten
- 1.28 to 1.65 aluminum
- 1.50 to 2.30 titanium
- up to 0.80 niobium
- 0.01 to 0.2 carbon
- up to 0.015 boron
- with a balance of nickel and impurities, the alloy further satisfying the following compositional relationships defined with elemental quantities being in terms of weight percent:
- 2.2<Al+0.56Ti+0.29Nb<2.9
- 6.5<Mo+0.52W<9.5
A nickel-chromium-cobalt based alloy, suitable for use in gas turbine transition ducts, having a composition in weight percent consisting essentially of:
- 17.5 to 21.3 chromium
- 8.3 to 14.2 cobalt
- 4.3 to 9.3 molybdenum
- up to 7.0 tungsten
- 1.29 to 1.63 aluminum
- 1.59 to 2.28 titanium
- up to 0.79 niobium
- 0.034 to 0.097 carbon
- 0.002 to 0.007 boron
- up to 2.6 iron
- with a balance of nickel and impurities, the alloy further satisfying the following compositional relationships defined with elemental quantities being in terms of weight percent:
- 2.35<Al+0.56Ti+0.29Nb<2.84
- 7.1<Mo+0.52W<9.3
An improved gas turbine engine of the type having a plurality of metal components wherein the improvement comprises at least one of the metal components is comprised in weight percent of:
- 17 to 22 chromium
- 8 to 15 cobalt
- 4.0 to 9.5 molybdenum
- up to 7.0 tungsten
- 1.28 to 1.65 aluminum
- 1.50 to 2.30 titanium
- up to 0.80 niobium
- 0.01 to 0.2 carbon
- up to 0.015 boron
- with a balance of nickel and impurities, the alloy further satisfying the following compositional relationships defined with elemental quantities being in terms of weight percent:
- 2.2<Al+0.56Ti+0.29Nb<2.9
- 6.5<Mo+0.52W<9.5
The improved gas turbine engine wherein the at least one of the metal components is a transition duct.
Dependencies are inferred from the claim text.