Abstract: A method of manufacturing a part with a CMAS-resistant thermal barrier coating (TBC) includes providing a part body having a surface and providing a source of coating material. The coating material includes a thermal protection material and a CMAS-reactive material. The method also includes delivering the coating material from the source toward the surface of the part body to form the CMAS-resistant TBC on the surface. The CMAS-resistant TBC includes both the thermal protection material and the CMAS-reactive material. The CMAS-reactive material is included as a substantially uniform distribution within the thermal protection material.

Abstract: A method of preparing a coated article is disclosed. The method includes depositing a coating composition on a surface of a substrate to form a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) thereon and give the coated article. The coating composition comprises from about 3 to about 50 wt. % of one or more rare-earth oxides, from about 45 to about 96.5 wt. % zirconia, and from about 0.5 to about 4 wt. % alumina, each based on the total weight of the coating composition. As deposited, the alumina is distributed substantially homogeneously throughout the CMAS-resistant TBC. A coated part prepared with the method is also disclosed.

Abstract: A method of providing a bond coat for a thermal barrier coating of a part of a turbomachine includes forming a first metallic bond coat layer on a substrate. The method also includes forming a second bond coat layer on the first metallic bond coat layer. The second bond coat layer has a porosity and a surface roughness that is greater than that of the first metallic bond coat layer. Furthermore, the method includes grit blasting the second bond coat layer to densify the second bond coat layer while substantially maintaining the surface roughness thereof.

Abstract: A method of manufacturing a part with a CMAS-resistant thermal barrier coating (TBC) includes providing a part body having a surface and providing a source of coating material. The coating material includes a thermal protection material and a CMAS-reactive material. The method also includes delivering the coating material from the source toward the surface of the part body to form the CMAS-resistant TBC on the surface. The CMAS-resistant TBC includes both the thermal protection material and the CMAS-reactive material. The CMAS-reactive material is included as a substantially uniform distribution within the thermal protection material.

Abstract: A method of manufacturing a part with a CMAS-resistant thermal coating includes providing a part body having a surface and forming a thermal barrier coating (TBC) layer on the surface. The method also includes providing a precursor of a CMAS-reactive material and depositing the CMAS-reactive material on the TBC layer using the precursor.

Abstract: A method of providing a bond coat for a thermal barrier coating of a part of a turbomachine includes forming a first metallic bond coat layer on a substrate. The method also includes forming a second bond coat layer on the first metallic bond coat layer. The second bond coat layer has a porosity and a surface roughness that is greater than that of the first metallic bond coat layer. Furthermore, the method includes grit blasting the second bond coat layer to densify the second bond coat layer while substantially maintaining the surface roughness thereof.