Material for components of a gas turbine
AssigneeMTU Aero Engines AG
InventorsWilfried Smarsly, Gerhard Sauthoff
Life of this patent
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Abstract
The presently described technology relates to a material for components of a gas turbine, in particular for components of a gas turbine aircraft engine, having a matrix of an iron-based alloy material, wherein the matrix of the iron-based alloy material being hardened by means of an intermetallic material of the Laves phase.
Claims20
A material for use as a component of a gas turbine system, said material having a matrix composed of an iron based alloy material, wherein the matrix composed of the iron based alloy material is hardened with an intermetallic material of the Laves phase, wherein the iron based alloy material comprises 31.0 to 91.9% by weight of iron, 6.0 to 40.0% by weight of aluminum, 2.0 to 25.0% by weight of chromium and 0.1 to 2.0% by weight of yttrium.
A material for use as a component of a gas turbine system, said material having a matrix composed of an iron based alloy material, wherein the matrix composed of the iron based alloy material is hardened with an intermetallic material of the Laves phase, wherein the iron based alloy material comprises 31.0 to 91.9% by weight of iron, 6.0 to 40.0% by weight of aluminum, 2.0 to 25.0% by weight of chromium and 0.1 to 2.0% by weight of hafnium.
A material for use as a component of a gas turbine system, said material having a matrix composed of an iron based alloy material, wherein the matrix composed of the iron based alloy material is hardened with an intermetallic material of the Laves phase, wherein the intermetallic material of the Laves phase comprises 15.0 to 65.0% by weight of iron, 1.0 to 15.0% by weight of aluminum, and 0.5 to 55.0% by weight of niobium.
Dependencies are inferred from the claim text.