A method of analyzing flow through a turbomachine which is suitable for computer programming is summarized. The method, which has been reported in NASA publications, is based on an equation for the velocity gradient along an arbitrary quasi-orthogonal rather than the normal to the streamline as used in previous methods. A quasi-orthogonal is defined to be any curve that intersects every streamline between the flow boundaries exactly once, as does an orthogonal to the streamlines. With this method a streamline analysis can be made on any given stream surface. A quasi-three-dimensional solution can be obtained by using the method for a hub-to-shroud analysis, followed by blade-to-blade analyses at hub, mean, and shroud. As an example, the method was applied to the radial-inflow turbine with splitter blades. The complete quasi-three-dimensional solution was obtained in a single computer run.

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