Abstract
The state of the boundary layers on the blade surfaces of the rotor of a radial inflow turbine has been investigated using surface-mounted hot-film anemometers. The boundary layers are shown to be laminar or intermittently turbulent at the design flow condition. This is despite the fact that the Reynolds number is relatively high and conventional two-dimensional numerical techniques predict transition at about 20% surface length. The boundary layer does not become fully turbulent because there is strong secondary flow and large acceleration of the flow close to the surface. Surface pressure distributions and an in viscid prediction method are used to assist in the explanation for the state of the boundary layers.
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