06725540 is referenced by 7 patents.
The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.