Repair of coated turbine components
AssigneeGeneral Electric Company
InventorsJeffrey A. Conner, Michael J. Weimer
Life of this patent
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Abstract
A gas turbine engine hot section component having a ceramic thermal barrier coating is repaired by removing the ceramic thermal barrier coating, removing oxidation products and corrosion products from the metallic bond coating beneath the ceramic thermal barrier coating, applying a noble metal to the component, diffusing the noble metal into the component substrate, and aluminiding the component to provide an outermost noble metal-Al layer.
Claims13
A method for repairing a gas turbine engine hot section component comprising an outer surface, a metallic bond coating over the outer surface, and a ceramic thermal barrier coating over the metallic bond coating, the method comprising:
- removing the ceramic thermal barrier coating;
- removing oxidation products and corrosion products from the metallic bond coating;
- applying a noble metal to the outer surface of the component;
- diffusing said noble metal into said outer surface;
- and
- aluminiding said outer surface to provide an outermost noble metal-Al layer.
A method for repairing a gas turbine engine hot section airfoil comprising an airfoil body, a metallic bond coating over the airfoil body, and a ceramic thermal barrier coating over the metallic bond coating, the method comprising:
- removing the ceramic thermal barrier coating;
- removing oxidation products and corrosion products from the metallic bond coating on the airfoil body;
- applying a layer of Pt to the airfoil body by plating;
- diffusing the Pt into the airfoil body;
- and
- aluminiding the airfoil body to provide an outermost PtAl layer.
A method for repairing a gas turbine engine hot section airfoil comprising an airfoil body, a metallic bond coating over the airfoil body, and a ceramic thermal barrier coating over the metallic bond coating, the method comprising:
- removing the ceramic thermal barrier coating;
- removing oxidation products and corrosion products from the metallic bond coating on the airfoil body;
- applying a layer of Pt having a thickness between about 0.0001 inch (0.00025 cm) and about 0.0004 inch (0.001 cm) to the airfoil body by plating;
- diffusing the Pt into the airfoil body;
- and
- aluminiding the airfoil body to provide an outermost PtAl layer having a thickness between about 0.002 inch (0.005 cm) and about 0.004 inch (0.010 cm).
Dependencies are inferred from the claim text.