Patent ID: 6881452
Filing Date: 2005-04-19
Classification: C23C,Y02T,Y10T

Abstract:
1. A method for coating a gas turbine component with a thermal barrier coating system by a controlled preoxidation heat treatment, comprising the steps of: providing a gas turbine component for use at high temperatures; applying a thin layer of platinum to at least a portion of a surface of the component; forming a single phase platinum aluminide on the surface of the component by exposing the thin layer of platinum to a source of aluminum for a preselected time; then, producing a surface of the single phase platinum aluminide having a surface finish between about 16 microinches R cleaning the single phase platinum aluminide to provide a surface free of oxides, contaminants and local gradients of nickel, aluminum and platinum; then, preoxidizing the single phase platinum aluminide by heating the component in a preselected partial pressure of oxygen, wherein the preoxidation is accomplished by heating the component to a preselected temperature at a preselected rate so as to form a thin layer of pure alumina over the single phase platinum aluminide; followed by, applying a ceramic top coat over the thin layer of pure alumina.