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Abstract

A theory for the development of the axial and peripheral velocity profiles in the early stages of an axial-flow compressor is presented. The theory assumes the existence of a stall-zone in the corner formed by the convex surface of each blade and the annulus wall. The extent along each blade of this stall-zone is assumed to be related to the theoretical annulus boundary layer thickness; equations are derived for predicting its growth through the blade roots and tips. The conditions at the blade ends are determined from the theory of a two-dimensional stalled cascade and the outlet angle variation is determined by momentum mixing. Actuator disc theory is then used to find the resulting flow. The predictions of this method are compared both with experimental results obtained from a three-stage compressor and with the predictions of secondary flow theory in which both loss and blade row entry velocity profile are taken from experiment. Somewhat better agreement between the stall-zone theory and experiment is found and to make the theory useful for designers the determination of a single parameter from experiment is indicated.

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Velocity Profile Development in Axial-Flow Compressors

Abstract

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