Publication number: 20100098865
Abstract: A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises at least one layer of a first material selected from the group consisting of a zirconate, a hafnate, a titanate, and mixtures thereof, which first material has been mixed with, and contains, from about 25 to 99 wt % of at least one oxide. The at least one oxide comprises at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, and yttrium. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
Type:
Application
Filed:
December 18, 2009
Publication date:
April 22, 2010
Applicant:
UNITED TECHNOLOGIES CORPORATION
Inventors:
David A. Litton, Kevin W. Schlichting, Melvin Freling, John G. Smeggil, David B. Snow, Michael J. Maloney