Abstract
In this report a method of analyzing subsonic inviscid flow between blades on a stream surface of revolution of a turbomachine, which may be an axial, a radial, or a mixed-flow type, is presented. There may be a change in thickness of stream surface of revolution in the through flow direction. The stream surface of revolution is mapped onto a plane. In this picture plane the influence of rotation of the system is not always represented by uniformly distributed vorticity. Instead, the distribution of vorticity varies with radius. For the calculation of velocity distribution in the picture plane, an available rotating annular cascade theory is modified so that the variation of vorticity with respect to radius is properly considered. Numerical examples for a mixed flow type compressor rotor are included.
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