METHOD FOR COOLING TURBINE BLADES OF A BLADE RING AND TURBINE BLADE SEGMENT FOR A TURBINE BLADE RING HAVING AT LEAST TWO AERODYNAMICALLY PROFILED BLADES

摘要

The invention relates to a method for cooling turbine blades of a turbine blade ring (13) and to a turbine blade segment (30) for a turbine blade ring (13), comprising a platform (31, 33) whereby the surface thereof comprises at least two aerodynamically profiled blades (32, 34, 46) that extend in a manner transversal in relation to said surface. Said blades have a pressure side wall (46) and a suction side wall (38) which extend respectively from a front edge (39) on the flow side to a rear edge (37) on the outflow side, in relation to the direction of flow of a hot gas (11) flowing around the blades (32, 34, 36). According to the invention, in order to provide a turbine blade segment (30) having an extended service life, one of the blades can not be traversed by a fluid.