Study of multilayer gradient thermal barrier coating of gas turbine blades and structural processes and failure mechanism leading under the high temperature
The important task for creating gas turbine engine is increasing efficiency. That is impossible without increasing gas operation temperature in the beginning of aircraft engine. Increasing the operation temperature requires creating an effective protection for each element of turbine construction from thermal stresses and thermal fatigue. One of the way to solve this problem is decreasing heat transmission from operation gas to each detail from the construction by applying multilayer thermal barrier coating. The study of gradient multilayer thermal barrier coating and failure mechanism is presented in this paper.