Abstract
In this study, delamination behavior of Thermal Barrier Coating (TBC) used in a high temperature component in a land based gas turbine was investigated experimentally and analytically. In the experiments, tensile test at some temperature conditions and fatigue test were performed. Two modes of crack initiation system could be observed depending on temperature. One mode was the crack initiating at bond coat/substrate interface and the other mode was the crack initiating at top coat/bond coat interface. It was found that delamination occurred in the segment between cracks and the delamination propagated along top coat/bond coat interface, which were depending on creep deformation.
