Gas turbine component with a thermal barrier coating, thermal barrier coating for a gas turbine component and method for producing a thermal barrier coating on a gas turbine component

摘要

The invention relates to a gas turbine engine part of an aircraft engine with a consisting of at least a first material body and applied to this body heat insulating layer, which consists of an oxide ceramic or has an oxide ceramic, incorporated to reduce the thermal conductivity of the thermal barrier microfaults and / or nanopoils in the oxide ceramic are.