Reflective coating and coating process therefor

A process for coating a turbine component of a gas turbine engine, comprising:

• applying a bond coat on a substrate of a component via electron beam physical vapor deposition;
• applying a thermal barrier material to the bond coat via electron beam physical vapor deposition to form a ceramic coating with a porous microstructure, the ceramic coating of a thickness from 100 microns to 200 microns (100,000-200,000 nm);
• and
• applying a precious metal as an optically opaque oxidation resistant conforming reflective layer onto the thermal barrier material via atomic layer deposition to a thickness of 1000-2000 angstroms (100-200 nm) such that the optically opaque oxidation resistant conforming reflective layer enters into 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, the conforming reflective layer conforming to the porous microstructure of the ceramic coating to a depth 20 times deeper than a gap opening of the porous microstructure, but not into physical contact with the substrate, wherein the precious metal is selected from the group consisting of platinum, platinum alloys, palladium, palladium alloys, rhodium, rhodium alloys, iridium, iridium alloys, osmium, ruthenium and mixtures thereof.