Engine hot section component and method for making the same
AssigneesROLLS-ROYCE plc, Rolls-Royce North America Technologies, Inc.
InventorsSubhash K. Naik, Charles J. Teague, James Carl Loebig
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Abstract
One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
Claims13
A method for manufacturing a gas turbine engine hot section component, the method comprising:
- selecting a first radiation barrier coating composition comprising tantalum oxide for a first refraction index;
- selecting a second radiation barrier coating composition comprising mullite for a second refraction index different from the first refraction index;
- performing a surface finish enhancing treatment on the gas turbine engine hot section component;
- and
- after performing the surface finish enhancing treatment, applying a plurality of pairs of alternating layers of the first radiation barrier coating composition and the second radiation barrier coating composition onto the gas turbine engine hot section component.
A method for manufacturing an engine hot section component, the method comprising:
- applying a thermal barrier coating (TBC) to the engine hot section component;
- performing a surface finish enhancing treatment on the TBC, wherein the surface finish enhancing treatment enhances reflective properties of the TBC;
- and
- after performing the surface finish enhancing treatment on the TBC, applying a plurality of pairs of alternating layers of a first radiation barrier coating composition and a second radiation barrier coating composition onto the TBC, wherein the first radiation barrier coating composition comprises tantalum oxide and has a first refraction index, and wherein the second radiation barrier coating composition comprises mullite and has a second, different refraction index.
Dependencies are inferred from the claim text.