Patent ID: 8449994
Filing Date: 2013-05-28
Classification: C04B,C23C,F01D,F05D,Y02T

Abstract:
1. A turbine engine component, comprising: a substrate; and a thermal barrier coating formed over the substrate, a majority of the thermal barrier coating comprising a multi-phase material, the multi-phase material comprising a polycrystalline material including two or more phases, wherein: each phase forms an individual grain, adjacent individual grains are separated by grain boundaries, each phase comprises an oxide compound, the multi-phase material is formed from three or more constituents, the three or more constituents consist of different materials that are not completely soluble in each other, the two or more phases are not completely soluble in each other and do not form only one compound, the three or more constituents comprise ZrO the two or more phases consist essentially of (Y+Ta)-doped tetragonal zirconia, yttrium tantalate YTaO