GAS TURBINE COMPONENT WITH A THERMAL BARRIER COATING, THERMAL BARRIER COATING FOR A GAS TURBINE COMPONENT AND PROCESS FOR PRODUCING A THERMAL BARRIER COATING ON A GAS TURBINE COMPONENT

摘要

The invention relates to a gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to said base body and consists of or includes an oxide ceramic, wherein micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.