Ni-Cr-Co alloy for advanced gas turbine engines
AssigneeHaynes International, Inc.
InventorLee Pike
Life of this patent
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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 9.1 molybdenum, up to 7 tungsten, 1.39 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, up to 3 iron, up to 1.5 tantalum and less than 0.02 zirconium, with a balance of nickel and impurities. Certain alloying elements must be present in amounts according to two equations here disclosed.
Claims33
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 9.1
- molybdenum
- up to 7.0
- tungsten
- 1.39 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
- up to 1.5
- tantalum
- less than 0.02
- zirconium
- 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≦9.1
A nickel-chromium-cobalt based alloy, suitable for use in gas turbine transition ducts, having a composition comprised in weight percent of:
- 17.5 to 21.3
- chromium
- 8.3 to 14.2
- cobalt
- 4.3 to 9.1
- molybdenum
- up to 7.0
- tungsten
- 1.39 to 1.65
- 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
- up to 1.5
- tantalum
- less than 0.02
- zirconium
- 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≦9.1
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 consisting essentially of:
- 17 to 22
- chromium
- 8 to 15
- cobalt
- 4.0 to 9.1
- molybdenum
- up to 7.0
- tungsten
- 1.39 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
- up to 1.5
- tantalum
- less than 0.02
- zirconium
- 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≦9.1
A nickel-chromium-cobalt based alloy having a composition comprised in weight percent of:
- 17 to 22
- chromium
- 8 to 15
- cobalt
- 7.9 to 9.1
- molybdenum
- up to 0.5
- tungsten
- 1.39 to 1.65
- aluminum
- 1.50 to 2.30
- titanium
- up to 0/5
- niobium
- 0.01 to 0.2
- carbon
- up to 0.015
- boron
- up to 1.5
- tantalum
- with the 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
- 8.0<Mo+0.52W≦9.0
A nickel-chromium-cobalt based alloys, suitable for use in gas turbine transition ducts, having a composition comprised in weight percent of:
- 17.5 to 21.3
- chromium
- 8.3 to 14.2
- cobalt
- 7.9 to 9.1
- molybdenum
- up to 0.5
- tungsten
- 1.39 to 1.63
- aluminum
- 1.59 to 2.28
- titanium
- up to 0.5
- niobium
- 0.034 to 0.097
- carbon
- 0.002 to 0.007
- boron
- up to 2.6
- iron
- up to 1.5
- tantalum
- 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
- 8.0<Mo+0.25W≦9.0
Dependencies are inferred from the claim text.