Thermal Barrier Coating (TBC) is a momentous element that influences the performance of gas turbine engine. This is designed to serve the purpose of protecting gas turbine components (especially combustor, stators and blades) from severe thermal environment. Turbine Entry Temperatures (TET) of gases can be higher than 1500K with TBCs providing a temperature drop of even higher than 200K across them. TBC has different layers like ceramic top coat, TGO, metallic bond coat and the metal substrate. These stacks together to form a basic TBC layer. In present research two blades with different stages has been coated for high temperature thermal analysis to check sustainability after coating. Even though combustion chambers also coated with high temperature sustainability additional advantages of coating on blades will decrease deterioration of blades and life time of blades will increase. A conceptual based linkage has been applied in research that overall performance of engine relates with turbine and compressor efficiencies.

Thermal Barrier Coating, Turbine Entry Temperature, Coating Structure.