Thermal barrier coating for gas turbine engine components
AssigneeRtx Corporation
InventorsChristopher W. Strock, Michael J. Maloney, David A. Litton, Benjamin Joseph Zimmerman, Brian T. Hazel
Life of this patent
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Abstract
A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include 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.
Claims20
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.
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 the thermal barrier coating includes a first porosity in a range of approximately 8% to 25% by volume and the outer layer includes a second porosity in a range of approximately 20% to 50% by volume.
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 by applying a plurality of individual coating sublayers, each individual coating sublayer having a thickness between 1 and 25 microns and formed with one of a plurality of individual coating passes of a suspension plasma spray device operated with a different set of spraying conditions from those used to form an adjacent individual coating sublayer, 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, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity.
Dependencies are inferred from the claim text.