Computation of Supercritical Compressor and Turbine Cascades with a Design Method for Transonic Flows

[+] Author and Article Information
E. Schmidt

Institut für Aerodynamik und Gasdynamik, Universität Stuttgart, Pfaffenwaldring 21, D-7000 Stuttgart 80, W. Germany

J. Eng. Power 102(1), 68-74 (Jan 01, 1980) (7 pages) doi:10.1115/1.3230236 History: Received December 08, 1978; Online September 28, 2009


The development of supercritical cascades follows experience with supercritical single profiles. In cascade arrangement strong inter-blade influences exist in the transonic region, so that a desired pressure distribution, starting from the contour shape, is not easy to realize. For these cases, a design method has been developed in which the boundary conditions can be prescribed in a simple and clear manner. Thickness and deflection are not restricted, since the full potential equation is treated. Variation of the axial velocity density ratio is provided for. The solution by relaxation leads to short computing times. Experimental comparisons for turbine and compressor cascades show the applicability of the method.

Copyright © 1980 by ASME
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