Abstract: A hollow turbine blade cooled with compressor air is divided into a cooling air chamber (6) and into impingement air cooling chambers (8, 9) by inner, supporting partitions (3, 4). The cooling air is conveyed from the cooling air chamber into the impingement air cooling chamber via impingement air channels (7) provided in the partitions. The impingement air channels are concave with regard to the adjacent outer wall (2) of the blade airfoil (1) and arranged completely in the hot area near the outer wall and, in addition, have an oblong or elliptical cross-section whose longitudinal axis agrees with the radial orientation of the turbine blade. By reduced stress concentration in the area of the impingement air channels, the fatigue and creep characteristics are improved and life is increased.

Abstract: A hollow-type turbine blade produced by a casting process has a cooling air cavity (8) and film cooling ducts (12) originating at this cooling air cavity (8). Adjacent film cooling ducts with a large length-diameter ratio are connected by cross-ducts (13) which are offset relative to each other and arranged vertically to the film cooling ducts. The casting mold comprises a core corresponding to a brickwall design of the film cooling ducts and the cross-ducts, with long core pins being intersupported by cross pins. The turbine blade, including all film cooling ducts, can be produced with high quality in a casting process.

Abstract: A hollow turbine blade cooled with compressor air is divided into a cooling air chamber (6) and into impingement air cooling chambers (8, 9) by inner, supporting partitions (3, 4). The cooling air is conveyed from the cooling air chamber into the impingement air cooling chamber via impingement air channels (7) provided in the partitions. The impingement air channels are concave with regard to the adjacent outer wall (2) of the blade airfoil (1) and arranged completely in the hot area near the outer wall and, in addition, have an oblong or elliptical cross-section whose longitudinal axis agrees with the radial orientation of the turbine blade. By reduced stress concentration in the area of the impingement air channels, the fatigue and creep characteristics are improved and life is increased.