Calcium-magnesium-alumino-silicate resistant thermal barrier coatings
A method for forming a coating system on a component includes depositing a reactive layer with predetermined CMAS reaction kinetics on at least a portion of a thermal barrier coating. The method also includes activating the reactive layer with a scanning laser. A component, such as a gas turbine engine component, includes a substrate, a thermal barrier coating and a reactive layer. The thermal barrier coating is deposited on at least a portion of the substrate. The reactive layer is deposited on at least a portion of the thermal barrier coating. The reactive layer has predetermined CMAS reaction kinetics activated by laser scanning.
1. A component subjected to elevated temperature during operation comprising:
a substrate;
a thermal barrier coating deposited on at least a portion of the substrate; and
a reactive layer deposited on at least a portion of the thermal barrier coating, the reactive layer having predetermined CMAS reaction kinetics activated by laser scanning.
2. A component as recited in claim 1 , wherein the reactive layer includes a CMAS powder mixture, wherein the powder mixture includes chemically conditioned CMAS and Y 2 Zr 2 O 7 .
3. A component as recited in claim 1 , wherein at least a portion of the reactive layer and a portion of the thermal barrier coating are fused when the reactive layer is activated by laser scanning.
4. A component as recited in claim 1 , further comprising a bond coat between the substrate and the thermal barrier coating.
5. A component as recited in claim 1 , wherein the thermal barrier coating includes a stabilized zirconia.
6. A component as recited in claim 1 , wherein the thermal barrier coating includes a stabilized zirconia having at least one crystallization promoting material selected from the group consisting of La 2 Zr 2 O 7 , GD 2 Zr 2 O 7 , Al 2 O 3 , TiO 2 , Y 2 Zr 2 O 7 , and mixtures thereof.
7. A component as recited in claim 1 , wherein the reactive layer includes at least one of Y 2 Zr 2 O 7 , GD 2 Zr 2 O 7 and TiO 2 .
8. A component as recited in claim 1 , wherein the component is a gas turbine engine component.
9. A component as recited in claim 1 , wherein the melt temperature of the reactive layer is at least 50 degrees Fahrenheit (10 degrees Celsius) higher than the melt temperature of environmental CMAS.
10. A component as recited in claim 1 , wherein the reactive layer has graded characteristics from an interface with the thermal barrier coating to an external surface of the reactive layer.