Turbine blade and gas turbine equipped with a turbine blade

A gas turbine, comprising:

• a flow duct extending along an axis of the turbine having an annular cross section for a working medium;
• and
• a plurality of blade stages having a plurality of annularly arranged turbine blades that extend radially into the flow duct arranged one after another along the axis of the turbine, wherein each turbine blade comprises:
• a blade leaf arranged along a blade axis having a blade tip, a foot opposite the tip, a suction side and a pressure side;
• a platform region arranged at the foot of the blade leaf;
• and
• a platform arranged at the platform region having a width and extends transversely with respect to the blade axis and partially formed by a first resilient and elastic material secured to a first abutment arranged on the blade leaf such that the first resilient elastic component forms a seal when installed between the first abutment and a second abutment arranged with an axially adjacent turbine blade, wherein the first abutment and the second abutment are each configured as a radial groove protruding in an axial direction of the rotor sufficient to resist an operative radial force of the respective first sheet metal component and the second sheet metal component.

A turbine blade, comprising:

• a blade airfoil section arranged along a blade axis having a blade tip, a root opposite the tip, a pressure side and a suction side opposite the pressure side;
• a platform region arranged at the root of the blade leaf;
• and
• a platform arranged at the platform region having a width and extending transversely with respect to the blade axis and partially formed by a first bendable metal component secured to a first abutment arranged on the blade leaf such that the sheet metal component forms a seal when installed between the first abutment and a second abutment arranged on an axially adjacent turbine blade, wherein the first abutment and the second abutment are each configured as a radial groove protruding in an axial direction of the rotor sufficient to resist an operative radial force of the respective first sheet metal component and the second sheet metal component.