Effects of Boundary Layer Controls on Stall Angle of Wells Turbine Blade

Abstract

Experimental investigations directed towards delaying stall onset of the wells self-rectifying air turbine are reported. Three boundarylayer controls have been tested in the two-dimensional cascade tunnel. These include (1) leading edge rotating cylinder, (2) leading edge slat and (3) breather slot. The flow visualization of wake behavior by paraffin mist method has suggested that the stall angle of Wells turbine may be increased by installing leading edge slats for the blades.