METHOD FOR PRODUCING A GAS TURBINE COMPONENT
A method for producing a gas turbine component, which comes into frictional contact with a friction partner, includes: providing a base body produced from a superalloy; applying a first metal coating to a surface of the base body facing the at least one friction partner in the mounted state, wherein an additive production method using a first metal powder is used to apply the first metal coating; and applying a second metal coating to the first metal coating, wherein an additive production method using a second metal powder and a pulverulent pore-forming agent is used to apply the second metal coating and, by adding the pore-forming agent, the porosity of the second metal coating is set such that it is greater than the porosity of the first metal coating, and the volume flows of the introduced metal powder and the introduced pulverulent pore-forming agent are set or controlled separately.
1 . A method for producing a gas turbine component, which in an intended mounted state comes in frictional contact with at least one friction partner during gas turbine operation, the method comprising:
providing a base body which is produced from a superalloy,
applying a first metal coating onto a surface of the base body, which surface faces toward the at least one friction partner in the intended mounted state, an additive manufacturing method using a first metal powder being employed for the application of the first metal coating;
applying a second metal coating onto the first metal coating, an additive manufacturing method using a second metal powder and a pore-forming agent in powder form being employed for the application of the second metal coating, and a porosity of the second metal coating being adjusted by the addition of the pore-forming agent in such a way that it is greater than the porosity of the first metal coating, and volume flow rates of the second metal powder and the pore-forming agent in powder form being adjusted or regulated separately.
2 . The method as claimed in claim 1 ,
wherein the first metal coating is applied using only the first metal powder, so that this coating is essentially pore-free.
3 . The method as claimed in claim 1 ,
wherein the first metal coating is applied with a thickness which does not exceed 200 μm.
4 . The method as claimed in claim 1 ,
wherein the volume flow rate of the pore-forming agent in powder form is adjusted or regulated during the application of the second metal coating in such a way that the porosity increases in an outward direction.
5 . The method as claimed in claim 1 ,
wherein during the application of the second metal coating, protruding structures are formed on that outer surface which faces toward the at least one friction partner in the intended mounted state.
6 . The method as claimed in claim 1 ,
wherein the first metal powder and the second metal powder are identical.
7 . The method as claimed in claim 1 ,
wherein the first metal powder and the second metal powder are an MCrAlY powder.
8 . The method as claimed in claim 1 ,
wherein the first metal coating and the second metal coating are applied by laser-beam deposition welding.
9 . The method as claimed in claim 1 ,
wherein titanium dihydride powder is used as a pore-forming agent in powder form.
10 . The method as claimed in claim 1 ,
wherein the gas turbine component is a guide ring segment and the at least one friction partner is a rotor blade, or vice versa.
11 . The method as claimed in claim 1 ,
wherein the superalloy comprises a nickel-based alloy.
12 . The method as claimed in claim 5 ,
wherein the protruding structures comprise webs.
13 . The method as claimed in claim 5 ,
wherein protruding structures comprise webs which extend in a circumferential direction in relation to the mounting state.
14 . The method as claimed in claim 5 ,
wherein protruding structures comprise webs which extend only in a circumferential direction in relation to the mounting state.