With corrosion resistant coating protected turbine component and method of making the same.

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A gas turbine engine component includes a substrate formed of a high temperature resistant material and a corrosion resistant layer. The corrosion resistant layer is inert to the molten salt impurities and includes a refractory metal vanadate of formula MxVyOz, wherein M is selected from the group consisting of alkaline earth metals, group IV and V transition metals, rare-earth metals and their combinations, and wherein z=x+2.5y, or z=1.5x+2.5y, or z=2x+2.5y.