Method for reconditioning a hot gas path part of a gas turbine

1. A method for reconditioning a hot gas path part of a gas turbine in order to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals, comprising:

providing a hot gas path part to be reconditioned;

removing a predetermined area of said hot gas path part, resulting in a cutout at said hot gas path part;

manufacturing a coupon or section for being inserted into said cutout to replace said removed area of said hot gas path part;

inserting said coupon or section into said cutout; and

joining said hot gas path part with said inserted coupon or section,

wherein said coupon or section is manufactured by a selective laser melting (SLM) method to obtain a fine grain sized material with improved low cycle fatigue (LCF) lifetime,

wherein said hot gas path part is coated, at least in an area comprising said inserted coupon or section, with a metallic overlay with improved thermo-mechanical fatigue (TMF) and oxidation lifetime,

wherein, in order to introduce a self-healing property, said metallic overlay comprises an additional active phase containing a melting point depressant and/or a substance with a softening point or melting point below an operation temperature or within an operation temperature range of said hot gas path part, and

wherein said coupon or section is completely over-aluminized by chemical vapor deposition (CVD).

2. The method as claimed in claim 1 , wherein said coupon or section is made of a higher oxidation resistant material than said hot gas path part.

3. The method as claimed in claim 2 , wherein said coupon or section is made of a highly precipitation strengthened Ni base superalloy.

4. The method as claimed in claim 3 , wherein said coupon or section is made of an MM247 alloy.

5. The method as claimed in claim 1 , wherein said metallic overlay is applied by

a) providing a powder material in which a portion of the powder material is sub-micron powder particles; and

b) applying said powder material to the surface of said hot gas path part by means of a thermal spraying technique to build up a coating layer.

6. The method as claimed in claim 5 , wherein said powder material is of the MCrAlY type with M=Fe, Ni, Co, or combinations thereof.

7. The method as claimed in claim 5 , wherein said powder material contains powder particles of micron size and/or larger agglomerates, and that the sub-micron powder particles are in said coating layer distributed around the surface of said powder particles of micron size and/or said larger agglomerates.

8. The method as claimed in claim 1 , wherein at least said area with said metallic overlay is additionally protected by applying a thermal barrier coating (TBC).

9. The method as claimed in claim 1 , wherein said hot gas path part is a front stage vane of a gas turbine, said vane comprising an airfoil with a leading edge and a trailing edge, and that at least part of said trailing edge is replaced by said coupon.

10. The method as claimed in claim 1 , wherein said hot gas path part is a front stage blade of a gas turbine, said blade comprising an airfoil with a leading edge and a trailing edge, and that at least part of said leading edge is replaced by said coupon.

11. The method as claimed in claim 1 , wherein the softening point or melting point is less than 1000 degrees Celsius.

12. The method as claimed in claim 1 , wherein the active phase has particles that are woven.

13. The method as claimed in claim 1 , wherein substances of the active phase include Chromium, Nickel, Aluminum, or a combination thereof.