To obtain the ultimate in performance from an axial compressor stage it is necessary that the operation of the blade rows comprising the stage be thoroughly understood. Appreciable advances have been accomplished in recent years, but much still remains to be done. This paper aims to present practical hypotheses concerning the nature of the flow between the blades and deals with design techniques in relation to this flow.

In addition, some elements of two-dimensional cascade data and a discourse on practical secondary flows are presented.

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