Cmas-resistant themal coating for part of gas turbine engine

A part with a thermal coating comprising:

• a part body;
• a thermal barrier coating (TBC) layer layered on the part body;
• and
• a plurality of precipitations of a CMAS-reactive material on the TBC.

A method of manufacturing a part of a gas turbine engine with a thermal coating comprising:

• providing a gas turbine engine part body, the gas turbine engine part having a surface;
• forming a thermal barrier coating (TBC) layer on the surface, the TBC layer including a rare-earth-doped zirconia ceramic, the TBC layer including a plurality of voids therein, the TBC layer defining an outer boundary;
• providing a soluble, metal-containing precursor of a CMAS-reactive material;
• creating a flow at least partly from the precursor provided;
• directing the flow to the TBC layer to condense a plurality of precipitations of the CMAS-reactive material on the TBC layer, at least some of the plurality of precipitations being condensed on the outer boundary, and at least some others of the plurality of precipitations being condensed within at least some of the plurality of voids.