Method for manufacturing components made of single crystal (SX) or directionally solidified (DS) nickelbase superalloys
View Patent ↗The invention relates to a method for manufacturing a component, especially of a gas turbine, made of a single crystal (SX) or directionally solidified (DS) nickelbase superalloy, including a heat treatment and a machining and/or mechanical treatment step. The ductility of the component is improved by doing the machining and/or mechanical treatment step prior to said heat treatment and a solution heat treatment of the component is done prior to the machining/mechanical treatment step.
1. A method for manufacturing a component comprised of a nickelbase superalloy, the nickelbase superalloy being one of: single crystal (SX) and directionally solidified (DS), the method comprising:
heating the component in a first heat treatment to a temperature below a gamma prime solvus temperature of the component, the first heat treatment comprising solution heat treatment;
machining at least one portion of the component after the first heat treatment;
mechanically treating the component after the first heat treatment;
heating the component in a second heat treatment after the machining and after the mechanically treating, the second heat treatment heating the component to a temperature that is below a gamma prime solvus temperature;
applying a coating onto at least one portion of the component;
performing a third heat treatment on the component after the coating is applied, the third heat treatment comprising at least one of: coating diffusion heat treatment and precipitation heat treatment.
2. The method of claim 1 , wherein the component is a component of a gas turbine.
3. The method of claim 1 , wherein the third heat treatment comprises both coating diffusion heat treatment and precipitation heat treatment.
4. The method of claim 3 , wherein the mechanically treating of the component comprises shot peening of at least one cooling channel defined in the component.
5. The method of claim 3 , wherein the component is a gas turbine blade.
6. The method of claim 5 , wherein the coating is applied onto an airfoil of the gas turbine blade.
7. The method of claim 6 , wherein the second heat treatment is a brazing heat treatment.
8. The method of claim 6 , wherein the at least one portion of the component that is machined is a portion of a fir tree of the gas turbine blade.
9. The method of claim 8 , wherein the mechanically treating of the component comprises mechanically treating at least one of the fir tree and a cooling channel of the gas turbine blade.
10. The method of claim 8 , wherein the third heat treatment heats the component to a temperature below a gamma prime solvus temperature of the component.
11. The method of claim 1 , wherein the component is a gas turbine blade and the coating is applied onto an airfoil of the gas turbine blade.
12. The method of claim 1 , wherein the machining and the mechanically treating of the component affects a surface of the component and the second heat treatment modifies a microstructure of the surface affected by the machining and the mechanically treating.
13. The method of claim 1 , wherein the third heat treatment heats the component to a temperature below a gamma prime solvus temperature of the component.