Method for manufacturing components made of single crystal (SX) or directionally solidified (DS) nickelbase superalloys

Patent metadata

Field	Value
Publication number	US-9670571-B2
Application number	US-201414493885-A
Country	US
Kind code	B2
Filing date	Sep 23, 2014
Priority date	Mar 27, 2012
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

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.

First claim

The invention claimed is:

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.

Assignees

• Alstom Technology Ltd
• Ansaldo Energia Ip Uk Ltd

Inventors

• Etter Thomas
• Mücke Roland

Classifications

• C30B29/52

  Alloys · CPC title

• F01D5/14

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F05D2300/606

  Directionally-solidified crystalline structures · CPC title

• C22C19/00

  Alloys based on nickel or cobalt · CPC title

• C21D2201/04

  Single or very large crystals · CPC title