Multilayer protective coating systems for gas turbine engine applications and methods for fabricating the same

A method of applying a multilayer protective coating to a substrate comprises the steps of:

• providing or obtaining a turbine engine component substrate formed of a ceramic material or a ceramic matrix composite material;
• depositing an environmental barrier coating layer comprising a rare earth disilicate material directly on the substrate;
• and
• depositing and sintering a plurality of pairs of alternating layers of the rare earth disilicate material and a rare earth monosilicate material directly on the environmental barrier coating layer,
• wherein each layer of the plurality of pairs of alternating layers is relative less thick as compared with the environmental barrier coating layer;
• wherein a single layer of the rare earth disilicate material defines an outermost surface of an entirety of the plurality of pairs of alternating layers.