Article and method of making thereof

A turbine engine component, comprising:

• a plurality of coatings disposed on a superalloy substrate comprising nickel, cobalt, or combinations thereof, the plurality of coatings comprising:
• a thermal barrier coating disposed on the superalloy substrate, wherein the thermal barrier coating comprises a ceramic thermal barrier coating material in a range from about 95 weight percent to about 100 weight percent, and wherein the ceramic thermal barrier coating material comprises yttria stabilized zirconia;
• a bond coating disposed between the substrate and the thermal barrier coating, wherein the bond coating comprises a metal aluminide or a M1CrAlY alloy, where M1 is iron, nickel, platinum, or cobalt;
• and
• a protective coating of a calcium-magnesium-aluminum-silicon-oxide (CMAS)-reactive material disposed on the thermal barrier coating, the CMAS-reactive material present in the protective coating in an amount of about 100 weight percent, the CMAS-reactive material is CaxSr1−xZr4(PO4)6, wherein x is a number from 0 to 1, and
• wherein the CMAS-reactive material is present in the plurality of coatings in an effective amount to react with a CMAS composition at an operating temperature of the thermal barrier coating, thereby forming a reaction product having one or both of melting temperature and viscosity greater than that of the CMAS composition.

An article, comprising:

• a substrate comprising a superalloy;
• a plurality of coatings disposed on the substrate, the plurality of coatings comprising:
• a thermal barrier coating disposed on the substrate, wherein the thermal barrier coating comprises a stabilized zirconia, and wherein the stabilized zirconia is present in the thermal barrier coating in a range from about 95 weight percent to about 100 weight percent,
• a bond coating disposed between the substrate and the thermal barrier coating, wherein the bond coating comprises a metal aluminide or a M1CrAlY alloy, where M1 is iron, nickel, platinum, or cobalt;
• and
• a protective coating of a calcium-magnesium-aluminum-silicon-oxide (CMAS)-reactive material disposed on the thermal barrier coating, the CMAS-reactive material present in the protective coating in an amount of about 100 weight percent, the CMAS-reactive material is CaxSr1−xZr4(PO4)6, wherein x is a number from 0 to 1.