Internal turbine component electroplating
AssigneeHowmet Corporation
InventorsWillard N. Kirkendall, Scott A. Meade, Donald R. Clemens
Life of this patent
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Abstract
Method and apparatus are provided for electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine component.
Claims18
A method of electroplating a surface area of a cooling cavity present in a gas turbine component, comprising positioning an electroplating mask on a region of the component where the cooling cavity has an open end to the exterior, extending an anode through the mask and cavity opening into the cooling cavity, extending a cathode through the mask to contact the component, and extending an electroplating solution supply conduit through the mask to supply electroplating solution to the cavity opening.
Apparatus for electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine component, comprising an electroplating mask disposed on a region of the component where the cooling cavity has a cavity open end to the exterior, an anode extending through the mask and the cavity opening into the cooling cavity, a cathode extending through the mask to contact the component, and an electroplating solution supply conduit extending through the mask to supply electroplating solution to the cavity opening.
A gas turbine engine airfoil component having a surface area of an internal wall defining a trailing edge cooling cavity therein, wherein the surface area has an electroplated metallic layer thereon.
Dependencies are inferred from the claim text.