| 摘要 |
PROBLEM TO BE SOLVED: To improve turbine efficiency by decreasing a collision loss of an operating gas that flows from a turbine scroll into a nozzle vane, at a nozzle vane tip end, and uniformizing the outflow stream of the gas at the rear end of the nozzle vane, and suppressing a collision loss and a secondary flow loss in a moving blade.SOLUTION: A radial turbine 1 includes a plurality of nozzle vanes 13 that are disposed in a circumferential direction inside a spiral scroll 3 and that adjust the flow of an operating gas from the scroll 3 to a moving blade 9. In the turbine 1, front edge bulging parts 25 are formed by bulging out the vicinities of both ends in the width direction of an inlet front edge 17 of the nozzle vane 13 to the pressure surface side of the nozzle vane compared to the central part of the nozzle vane to match the gas inflow angle of the operating gas flowing into the nozzle vane 13. Further, back edge bulging parts 29 are formed by bulging out the vicinities of both ends in the width direction of the outlet back edge 27 of the nozzle vane 13 to the pressure surface side compared to the central part of the nozzle vane. |
