METHODS FOR FORMING HIGH TEMPERATURE COATING SYSTEMS AND GAS TURBINE ENGINE COMPONENTS INCLUDING THE

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Methods for forming high temperature coating systems are provided, as are gas turbine engine components including high temperature coating systems. In embodiments, the coating formation method includes forming a fracture-resistant Thermal Barrier Coating (TBC) layer over a workpiece surface. The fracture-resistant TBC layer is produced from a first coating precursor material containing an amount of zirconia in mole percent (ZrOmol %1) and an amount of tantala in mole percent (TaOmol %1). A Calcium-Magnesium Aluminosilicate (CMAS) resistant TBC layer is formed over the fracture-resistant TBC layer from a second coating precursor material, which contains an amount of zirconia in mole percent (ZrOmol %2), an amount of tantala in mole percent (TaOmol %2), and an amount of one or more rare earth oxides in mole percent (REOmol %2). The first and second coating precursor materials are formulated such that ZrOmol %1 is greater than ZrOmol %2, TaOmol %1 is less than TaOmol %2, and TaOmol %2 is substantially equivalent to REOmol %2.