Gas turbine

Abstract

A gas turbine having at least one disk, wherein turbine blade elements are connected via connection means to the at least one disk, wherein the connection means are arranged in the interior of the turbine blade elements in a region radially above the disk in the radial direction of the turbine blade elements, in particular in a region which is in the driving airflow during the operation of the gas turbine, and the turbine blade elements have at least two zones composed of different materials, wherein the at least two zones adjoin one another in particular in the radial direction, and in that a zone with a material suited to compressive stress, in particular a ceramic, in particular an yttrium-stabilized zirconium oxide, is arranged radially below the connection means, and a zone with a material suited to tensile stress, in particular CMSX 4, is arranged radially above the connection means.

Dependencies are inferred from the claim text.