A method for predicting the deviation angle at exit from the nozzles of an inward flow radial turbine using a streamline curvature method is given. Measurements of flow angles and stagnation and static pressures across the nozzle exit span of a small turbine have been made. The accuracy of the analysis is shown by comparison with experimental results. Finally, the developed theory has been used to show the possible effect on the deviation angle at exit from the nozzles of reducing the number of stator blades.

This content is only available via PDF.