Material for a gas turbine component, method for producing a gas turbine component and gas turbine component
A material for a gas turbine component, to be specific a titanium-aluminum-based alloy material, including at least titanium and aluminum. The material has a) in the range of room temperature, the β/B2-Ti phase, the α 2 -Ti 3 Al phase and the γ-TiAl phase with a proportion of the β/B2-Ti phase of at most 5% by volume, and b) in the range of the eutectoid temperature, the β/B2-Ti phase, the α 2 -Ti 3 Al phase and the γ-TiAl phase, with a proportion of the β/B2-Ti phase of at least 10% by volume.
1. A material for a gas turbine component, comprising:
titanium; and
aluminum;
wherein:
a) the material has, in a range of room temperature, a β/B2-Ti phase, a α2-Ti 3 Al phase, and a γ-TiAl phase, with a proportion of the β/B2-Ti phase of at most 5% by volume;
b) and the material has, in a range of eutectoid temperature, the β/B2-Ti phase, the α2-Ti 3 Al phase, and the γ-TiAl phase, with a proportion of the β/B2-Ti phase of at least 10% by volume.
2. The material according to claim 1 , wherein a proportion of a body-centered cubic β/B2-Ti phase in the range of room temperature is less than 5% by volume.
3. The material according to claim 1 , wherein a proportion of a body-centered cubic β/B2-Ti phase in the range of eutectoid temperature is greater than 10% by volume.
4. The material according to claim 1 , wherein the β/B2-Ti, the α 2 -Ti 3 Al, and the γ-TiAl phases are present in the range of room temperature.
5. The material according to claim 1 , wherein the β/B2-Ti, the α 2 Ti 3 Al, and the γ-TiAl phases are in thermodynamic equilibrium in the range of eutectoid temperature.
6. The material according to claim 1 , further comprising:
niobium;
molybdenum and/or manganese; and
boron and/or carbon and/or silicon.
7. The material according to claim 6 , wherein the material has:
42 to 45 atomic percent aluminum;
3 to 8 atomic percent niobium;
0.2 to 3 atomic percent molybdenum and/or manganese;
0.1 to 1 atomic percent boron and/or carbon and/or silicon; and
a remainder of titanium.
8. The material according to claim 1 , wherein a forming temperature of the material lies between T e −50 K and T a +100 K, wherein T e is the eutectoid temperature of the material and T a is the alpha transus temperature of the material.
9. A method for producing a gas turbine component, comprising the steps of:
a) making available a semi-finished product from the material according to claim 1 ; and
b) forging the semi-finished product from the material into a component at a forming temperature between T e −50 K and T a +100 K, wherein T e is the eutectoid temperature of the material and T a is the alpha transus temperature of the material.
10. The method according to claim 9 , wherein the forging is carried out at a forming rate of at least 1 m/s.
11. The method according to claim 9 , wherein a heat treatment is carried out following the forging.
12. The method according to claim 9 , wherein a cast semi-finished product is used as the semi-finished product.
13. A gas turbine component made of the material according to claim 1 and produced by the method according to claim 9 .
14. The gas turbine component according to claim 13 , wherein the component is a blade, which is singly forged in a region of a blade pan for making a rougher microstructure with high creep resistance available, and which is multiply forged in a region of a blade root for making a finer microstructure with high ductility available.