Internal airfoil component electrolplating

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 airfoil component.

The invention claimed is: 
     
       1. A gas turbine engine airfoil component having an internal wall defining a cooling cavity within the component, the cooling cavity extending a length between a first end and a second end of the component, the internal wall having a first surface area extending along a first preponderant portion of the length of the cooling cavity and a second surface area extending along a second preponderant portion of the length of the cooling cavity, the first surface area having an electroplated metallic layer, the second surface area being un-plated by the electroplated metallic layer. 
     
     
       2. The component of  claim 1  wherein the electroplated metallic layer is a noble metal. 
     
     
       3. The component of  claim 1  wherein the component is a gas turbine engine blade or vane or segment of a blade or vane. 
     
     
       4. The component of  claim 1  wherein the first surface area is aluminized. 
     
     
       5. The component of  claim 1 , further comprising cooling air exit passages extending through the wall and communicating with the cooling cavity. 
     
     
       6. The component of  claim 5 , wherein the cooling air exit passages are electroplated with a metallic layer. 
     
     
       7. The component of  claim 6 , wherein the cooling air exit passages are aluminized. 
     
     
       8. The component of  claim 5 , wherein the second surface area is disposed distal to the cooling air exit passages. 
     
     
       9. The component of  claim 1 , wherein the wall has a third surface area disposed at an angle relative to the first surface area and the second surface area, the third surface area lacking an electroplated metallic layer. 
     
     
       10. The component of  claim 1 , wherein the first surface area is disposed across the cooling cavity distal to the second surface area. 
     
     
       11. The component of  claim 10 , wherein the first surface area is disposed opposite to the second surface area. 
     
     
       12. The component of  claim 1 , wherein the first end of the cooling cavity is open and the second end of the of the cooling cavity is closed.