| 摘要 |
PROBLEM TO BE SOLVED: To suppress loss caused by enlarging a nozzle flow-in angle in the vicinity of both wall surfaces of a hub side and a shroud side, in a radial turbine having a plurality of nozzles for forming a flow-in passage for a turbine moving blade of a fluid such as gas for rotatably driving a turbine moving blade. SOLUTION: The shape of a plurality of nozzles 3 for forming a flow-in passage for a fluid such as gas for rotatably driving a turbine moving blade, has larger blade angle 7a in the vicinity of a hub side wall surface 3a and a shroud side wall surface 3b part of a nozzle front edge than a blade angle 7b in the center passage. Accordingly, an incidence angle of flow formed in the vicinity of both wall surfaces of a hub side and a shroud side is reduced, and nozzle loss is also reduced.
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