US 11,852,078 B2
Reflective coating and coating process therefor
Brian T. Hazel, Avon, CT (US); Alan C. Barron, Jupiter, FL (US); and Mary Catherine Gurak, Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jun. 30, 2021, as Appl. No. 17/363,958.
Application 17/363,958 is a division of application No. 16/433,896, filed on Jun. 6, 2019, granted, now 11,053,855.
Prior Publication US 2021/0324800 A1, Oct. 21, 2021
Int. Cl. C23C 14/30 (2006.01); F02C 7/24 (2006.01); C23C 14/08 (2006.01); C23C 16/06 (2006.01); C23C 16/455 (2006.01)
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
OG exemplary drawing
 
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.