| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine stage structure of an axial flow compressor capable of reducing pressure loss of working fluid sufficiently to improve performance of the compressor and to provide a gas turbine using it. SOLUTION: In this turbine stage structure of the axial flow compressor constituted by arranging stationary blades 11 and moving blades 13 alternately at many steps through a hub shroud cavity 14, swirlers 15a, 15b for reducing interference with a main stream of working fluid by giving swirl to leaking flow jetted from a port for leaking flow are provided on hub side walls 13a, 13a on a moving blade side as a pressure loss reducing means for reducing pressure loss of the main stream of working fluid passing through above the port for leaking flow in the hub shroud cavity. COPYRIGHT: (C)2006,JPO&NCIPI
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