Internal airfoil component electroplating

1. A method of electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine airfoil component, comprising positioning an anode residing on an electrical insulating anode support in the cooling cavity of the component, which is a cathode, with a base surface of the anode support engaging another surface area of the internal wall to mask said another surface area from being electroplated and to position the anode relative to said surface area to be electroplated and with a masking shield extending from the anode support to mask a closed-end surface area of the internal wall from being electroplated, and flowing a noble metal-containing electroplating solution into the cooling cavity during at least part of an electroplating time to deposit a layer of noble metal on said surface area.

2. The method of claim 1 wherein the electroplating solution includes a metal comprising Pt, Pd, Au, Ag, Rh, Ru, Os, or Ir to deposit said metal on said surface area.

3. The method of claim 1 wherein the electroplating solution is supplied to the cooling cavity via a supply conduit having one or more back pressure relief openings.

4. The method of claim 1 wherein the anode comprises nickel when the component is made of Ni base superalloy.

5. The method of claim 1 wherein the component comprises a gas turbine engine vane or blade or segment thereof.

6. The method of claim 1 including the further step of aluminizing the electroplated surface area to form a diffusion aluminide coating having the noble metal incorporated therein.

7. The method of claim 1 wherein the anode extends through an anode locator rib located at one end of the anode support and has an anode end that is received in an opening in the masking shield located at another end of the anode support.

8. The method of claim 7 wherein the anode is rod-shaped.