THERMAL BARRIER COATING SYSTEM, GAS TURBINE COMPONENT AND METHOD FOR COATING A GAS TURBINE COMPONENT

摘要

A thermal barrier coating system for a gas turbine component with a plurality of coats arranged one over one another, wherein the thermal barrier coating system comprises in sequence, proceeding from the base material (1) of the gas turbine component, the following coats: a) a metal bonding coat (2); b) a porous ceramic intermediate coat (3); c) a reflection coat (4) with a photonic crystal made of a ceramic material; d) a porous ceramic top coat (5).