Patent ID: 8602741

Claim:
A turbine blade for a stationary gas turbine, the turbine blade comprising: a platform section connected to a fastening section, the platform section comprising a platform with a platform surface, a blade being arranged on the platform surface, the blade being profiled in a cross section and including a pressure-side wall and a suction-side wall; an outer rounding, wherein surfaces of the pressure-side wall and of the suction-side wall, which are exposable to a hot gas, merge into the platform surface via the outer rounding; a cavity arranged in the blade and extending into the platform section; and a rib which connects the pressure-side wall to the suction-side wall, the rib being arranged in the cavity, and the rib sub-dividing the cavity along a longitudinal direction of the blade, wherein, at a level of the outer rounding, a platform-side rib end extends by a different distance on an inner side of the pressure-side wall than on an inner side of the suction-side wall, wherein the platform surface is part of an imaginary platform plane which extends through the cavity, and wherein the platform-side end of the rib lies on a pressure side on one side of the platform plane and lies on a suction side on the other side of the platform plane.