Coated turbine blade

An axial-flow gas turbine engine, comprising:

• a rotatably mounted rotor arranged along a rotational axis of the engine;
• a plurality of compressor blades arranged on the rotor to form an axial-flow compressor section, wherein a working medium is compressed;
• a combustion section that receives the compressed working medium, mixes the compressed working medium with a fuel and combusts the mixture to form a hot working medium;
• a plurality of hollow turbine blades and vanes arranged to form an axial-flow turbine section where the turbine section receives the hot working medium and expands the hot working medium, wherein the plurality of turbine blades and vanes have:
• a hollow airfoil section formed by a suction side blade wall and a pressure side blade wall,
• a coating arranged on an outer surface of the pressure side and suction side blade walls that faces the hot working medium, and
• a support rib arranged in a connecting region inside the hollow airfoil section that connects the pressure side and suction side blade walls, where a thickness of the coating in a region of the outer surface opposite each of the connecting regions has a greater layer thickness than a further region of the outer surface of the blade walls that define a cavity inside the hollow airfoil section.