CPC F02C 7/24 (2013.01) [C23C 14/083 (2013.01); C23C 14/30 (2013.01); C23C 16/06 (2013.01); C23C 16/45525 (2013.01); F05D 2220/32 (2013.01); F05D 2230/31 (2013.01); F05D 2300/1431 (2013.01); F05D 2300/1432 (2013.01); F05D 2300/1433 (2013.01); F05D 2300/1434 (2013.01); F05D 2300/1435 (2013.01)] | 12 Claims |
1. A gas turbine engine component, comprising:
a substrate;
a ceramic coating comprising a thermal barrier material on the substrate; and
an optically opaque oxidation resistant conforming reflective layer conforming to a porous microstructure of the ceramic coating, the conforming reflective layer comprising a platinum group metal on the thermal barrier material in an interconnected porosity of the ceramic coating, the optically opaque oxidation resistant conforming reflective layer having a melting point higher than a use temperature of the ceramic coating to reduce radiation heat transport of the ceramic coating, wherein the conforming reflective layer penetrates to a depth 20 times a depth of a gap opening of the porous microstructure.
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