A quasi-three-dimensional solution method is presented for subsonic flows through turbomachines of arbitrary geometry. Principal equations are based on Wu’s formulation of flow on blade-to-blade and hub-to-shroud surfaces, modified such that the same hub-to-shroud principal equation is used for all types of stream surfaces. Blade-to-blade surfaces are assumed to be surfaces of revolution. A stream function is used as the field variable. The problem is solved by finite element method. An iterative solution is used to find the quasi-three-dimensional solution. Solutions at hub, tip and mid height blade-to-blade surfaces are used to construct a mean hub-to-shroud surface and vice versa, until convergence is obtained. Results indicate that the developed technique is satisfactory for predicting the flow through turbomachine blades.
A Quasi-Three-Dimensional Finite Element Solution for Steady Compressible Flow Through Turbomachines
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Ücer, AS, Yeġen, İ, & Durmaz, T. "A Quasi-Three-Dimensional Finite Element Solution for Steady Compressible Flow Through Turbomachines." Proceedings of the ASME 1982 International Gas Turbine Conference and Exhibit. Volume 1: Turbomachinery. London, England. April 18–22, 1982. V001T01A089. ASME. https://doi.org/10.1115/82-GT-261
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