Thermal protection methods using barrier coatings with strain tolerance grooves

A method of fabricating a turbine engine component, the method comprising:

• applying a thermal barrier coating to the component to facilitate decreasing heat transfer to the component, wherein the thermal barrier coating comprises at least one thermal insulating layer and a metallic bond coat layer, wherein the at least one thermal insulating layer extends across the metallic bond coat layer and wherein the metallic bond coat layer is in contact with an outer surface of the component;
• forming a plurality of grooves in the at least one thermal insulating layer of the applied thermal barrier coating to facilitate increasing a strain tolerance of the thermal barrier coating, wherein each of the plurality of grooves extends into a depth into the at least one thermal insulating layer to a groove bottom along a line perpendicular to the metallic bond coat layer;
• and
• depositing a material within the plurality of grooves to facilitate increasing an amount of thermal protection of the metallic bond coat layer that is proximate to the line of extension of each of the plurality of grooves.