An Approach for Improvement of Non-Steady State Thermo-Mechanical Fatigue Life for Thermal Barrier Coated Structure

Abstract

Thermal stress was analyzed when a gas turbine thermal barrier coated structure was subjected to a sudden change in combustion gas temperature. The thermal stress was calculated based on the third kind boundary condition by the Biot number. The numerical calculation showed that the transient thermal stress magnitude was significantly affected by the Biot number, and that it should be distinguished from the steady state thermal stress. The influence of physical properties in TBCs was also examined quantitatively.