Turbine blade for a gas turbine

摘要

For the purpose of cooling in the case of a turbine blade (1) for a gas turbine, cooling air is guided through a cooling air duct (5), arranged in the interior of the blade, to the front edge (leading edge) (2) of the blade and blown off to the outside in the region of the front edge (2) through cooling air openings (9), orientated virtually parallel to the outer side (3, 4) of the turbine blade (1), in such a way that a cooling air film is formed on the outer side (3, 4) and the front edge (2) is cooled exclusively from the inside out by means of the cooling air guided to the cooling air openings (9). An improvement in cooling is achieved in said turbine blade when in the flow direction there is let into the blade wall (18) downstream of the front edge (2) at least on one side a step (8) which extends parallel to the front edge (2) and is bounded by two side faces (8a, b) of which the side face (8a) at the front in the flow direction is orientated virtually at right angles, and the side face (8b) downstream in the flow direction is orientated virtually tangentially to the outer side (3, 4), and when the cooling air openings (9) are arranged inside the front side face (8a).