| 摘要 |
A GAS TURBINE BLADE (1) HAS A SHROUD (3) WHICH IS COOLED BY DIFFERENT COOLING MECHANISMS IN VARIOUS REGIONS (A, B, C) ACCORDING TO THE DIFFERENT THERMAL LOAD. IN A FIRST REGION (A) IN A FIN (8) , BORES ARE PROVIDED, BY MEANS OF WHICH A CONVECTIVE COOLING OF THE FIN AND A FILM COOLING OF THE HOT GAS SIDE OF THE FIN ARE IMPLEMENTED. A SECOND REGION (B) IS COOLED BY MEANS OF IMPINGEMENT COOLING BY A COOLING AIR STREAM FROM A DUCT IN THE RADIALLY OPPOSITE STATOR HOUSING. A THIRD REGION (C) HAS A PLURALITY OF BORES RUNNING PARALLEL WHICH RUN FROM A COOLING DUCT OF A COOLING SYSTEM FOR THE BLADE LEAF TO THE RADIALLY OUTER SURFACE OF THE SHROUD. A COOLING AIR STREAM FLOWING THROUGH THESE BORES CAUSES A CONVECTIVE COOLING OF THIS REGION.
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