Abstract: Ceramic thermal barrier coatings (TBCs) have been increasingly used to extend the durability of aircraft gas turbine engine. This not only increases components lifetime, but also allows higher engine temperatures and therefore better efficiency. Compared with the plasma spray technique, the electron beam physical vapor deposition has led to the incorporation of very durable coatings on the most demanding rotating turbine components. The failure mode and the thermal barrier effect of TBCs are also discussed.

Key words: TBCs, ZrO₂, gas turbine blades