Patent ID: 8221825
Filing Date: 2012-07-17
Classification: C23C,F01D,F05D

Abstract:
1. A method for the local initial application of a thermal barrier coating layer, or the local repair of coating defects and/or deteriorations, of components in the hot gas path of a gas turbine engine, which components are at least locally coated or to be coated with a thermal barrier coating layer, the method comprising: (III) locally applying a ceramic tissue and a wet chemical thermal barrier coating layer deposition material to a location of said component, forming a patch of ceramic matrix composite; (IV)a optionally inspecting said patch, the surface of the component, or both; (IV)b optionally locally applying at least one additional ceramic tissue and a wet chemical thermal barrier coating layer deposition material, forming at least one additional patch of ceramic matrix composite, at said location; (V) optionally surface finishing at said location; and (VI) optionally inspecting said location; wherein, in addition to step (III), at least one of steps (IV)a or (VI) is performed; wherein said locally applying a ceramic tissue and a wet chemical thermal barrier coating layer deposition material comprises infiltrating the ceramic tissue with the wet chemical thermal barrier coating layer deposition material prior to, during, after, or combinations thereof, said applying the ceramic tissue to said location; and wherein said infiltrating the ceramic tissue with the wet chemical thermal barrier coating layer deposition material comprises