US 12,344,938 B2
Thermal barrier coating for gas turbine engine components
Christopher W. Strock, Kennebunk, ME (US); Michael J. Maloney, Marlborough, CT (US); David A. Litton, West Hartford, CT (US); Benjamin Joseph Zimmerman, Moseley, VA (US); and Brian T. Hazel, Avon, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Jun. 28, 2021, as Appl. No. 17/359,855.
Application 17/359,855 is a division of application No. 13/603,891, filed on Sep. 5, 2012, granted, now 11,047,033.
Prior Publication US 2021/0324506 A1, Oct. 21, 2021
Int. Cl. C23C 4/02 (2006.01); C23C 4/11 (2016.01); C23C 4/134 (2016.01); C23C 28/00 (2006.01); F01D 5/28 (2006.01)
CPC C23C 4/02 (2013.01) [C23C 4/11 (2016.01); C23C 4/134 (2016.01); C23C 28/321 (2013.01); C23C 28/3215 (2013.01); C23C 28/3455 (2013.01); C23C 28/347 (2013.01); F01D 5/288 (2013.01); F05D 2300/13 (2013.01); F05D 2300/514 (2013.01); Y10T 428/249981 (2015.04); Y10T 428/31678 (2015.04)] 20 Claims
OG exemplary drawing
 
1. A method of coating a component of a gas turbine engine, comprising:
applying a thermal barrier coating onto at least a portion of a substrate of the component; and
applying an outer layer onto at least a portion of the thermal barrier coating using the same application technique used to apply the thermal barrier coating, wherein the outer layer includes a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer, wherein said thermal barrier coating includes a first priority in a range of approximately 20% to 28% by volume and said outer layer includes a second priority in a range of 40% to 60% by volume.