Airfoil for turbine vane or turbine blade of an axial gas turbine

Abstract

The present invention relates to an airfoil AF for a turbine vane or turbine blade of a gas turbine comprising a suction and a pressure side wall (SW, PW). The pressure and side walls extend from a leading edge LE to a trailing edge TE and from an inner end (IE,fig.2) to an outer end (OE,fig.2). The airfoil comprises at least one first feed plenum FP1 for a coolant and at least two cooling circuits (CC1,CC2) in flow connection with the at least one feed plenum. The cooling circuits are located in the suction and / or pressure side wall. Each cooling circuit comprises a number of channel sections CS and an outlet region (OR1,OR2,fig.2), in which the most downstream arranged channel sections of the respective cooling circuit open out into one the suction and / or pressure side wall of the airfoil. The outlet regions are separated from one another. The airfoil also comprises an overlapping region (PR,fig.2) in which the channel sections of different cooling circuits overlaps, the channel sections of the different cooling circuits are arranged alternatingly in a regular pattern.

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