RADIAL TURBINE

摘要

In order to reduce impact loss of a working gas flowing from a turbine scroll into nozzle vanes at the front-end part of the nozzle vanes and to achieve a uniform outflow at the rear-end part of the nozzle vanes, thereby suppressing collision loss and secondary flow loss at the rotor blades and improving turbine efficiency, a radial turbine (1), which is equipped with multiple nozzle vanes (13) that are arranged in the circumferential direction inside a spiral scroll (3) and adjust the flow of a working gas from the scroll (3) to the rotor blades (9), is characterized in that front edge bulging sections (25) are formed by bulging out the area near both widthwise ends of the inlet front edge sections (17) of the nozzle vanes (13) in the width direction of so as to bulge out more at the pressure-surface side of the nozzle vane than at the center part thereof, thereby matching the inflow angle of the working gas flowing into the nozzle vanes (13), and rear edge bulging sections (29) are formed after bulging out the area near both widthwise ends of the outlet rear edge sections (27) of the nozzle vanes (13)so as to bulge out more at the pressure-surface side than at the center part.