The boundary layers at a turbine runner outlet and their evolution with the operating points are unknown and represent an important factor for the pressure recovery of the elbow diffuser. To characterize the boundary layer, a hot film probe is used. The measurement accuracy is an important aspect of this study and the measurement procedure is exposed. An experimental campaign is realized in a turbine cone in order to characterize the wall friction evolution for 4 operating points. Both steady and transient analysis of the experimental results are presented.

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