In the calculation of the flow in a turbomachine, empirical correction factors have previously been used to allow for the effect of the annulus wall boundary layers. A calculation method has been produced which includes the estimation of the growth of the boundary layers and the associated secondary flows. The results from an experimental investigation of the flows past a row of inlet guide vanes and an isolated rotor row are compared with the theoretical predictions. The agreement is good except for the growth of the boundary layer where the swirl is high.

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