Reflective coating and coating process therefor

Patent metadata

Field	Value
Publication number	US-11053855-B2
Application number	US-201916433896-A
Country	US
Kind code	B2
Filing date	Jun 6, 2019
Priority date	Jun 6, 2019
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.

First claim

What is claimed:

1. A process for coating a component of a gas turbine engine, comprising:
applying a thermal barrier material to form a ceramic coating with a porous microstructure on a substrate, the ceramic coating of a thickness from 100 microns to 200 microns; and
applying a platinum group metal as an optically opaque oxidation resistant conforming reflective layer onto the thermal barrier material to enter 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 from one-quarter to three-quarters the way down the porous microstructure, but not into physical contact with the substrate, wherein the platinum group metal is formed from a precious metal selected from the group consisting of platinum, platinum alloys and mixtures thereof.

2. The process as recited in claim 1 , further comprising penetrating the conforming reflective layer to a depth 20 times deeper than a gap opening of the porous microstructure of the ceramic coating.

3. The process as recited in claim 1 , further comprising applying the thermal barrier material via electron beam physical vapor deposition.

4. The process as recited in claim 1 , further comprising conforming the conforming reflective layer to an open porosity and gaps of the porous microstructure of the ceramic coating.

5. The process as recited in claim 1 , wherein the conforming reflective layer minimum thickness is 80 nm.

6. The process as recited in claim 1 , wherein the conforming reflective layer is 1000-2000 angstroms thick.

7. 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.

8. The process as recited in claim 7 , further comprising penetrating the conforming reflective layer to a depth from one-quarter to three-quarters the way down the porous microstructure.

9. The process as recited in claim 7 , wherein the platinum group metal is formed from a precious metal selected from the group consisting of platinum, platinum alloys and mixtures thereof.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Hazel Brian T
• Barron Alan C
• Gurak Mary Catherine

Classifications

• F05D2300/1431

  Palladium · CPC title

• F02C7/24 Primary

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F05D2300/1434

  Iridium · CPC title

• F05D2300/1433

  Osmium · CPC title

• C23C16/45525

  Atomic layer deposition [ALD] · CPC title