A Rapid Blade-to-Blade Solution for Use in Turbomachinery Design

[+] Author and Article Information
E. R. McFarland

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio 44135

J. Eng. Gas Turbines Power 106(2), 376-382 (Apr 01, 1984) (7 pages) doi:10.1115/1.3239574 History: Received December 21, 1982; Online October 15, 2009


A rapid technique for solving the blade-to-blade turbomachinery flow problem has been developed. Approximate governing flow equations, which include the effects of compressibility, radius change, rotation, and variable stream sheet thickness are solved using an improved panel method. The development and solution of these equations are described. Sample calculations are presented to illustrate the method’s capabilities and accuracy.

Copyright © 1984 by ASME
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