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RESEARCH PAPERS

Full Potential Solution of Transonic Quasi-Three-Dimensional Flow Through a Cascade Using Artificial Compressibility

[+] Author and Article Information
C. Farrell, J. Adamczyk

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

J. Eng. Power 104(1), 143-153 (Jan 01, 1982) (11 pages) doi:10.1115/1.3227243 History: Received December 08, 1980; Online September 28, 2009

Abstract

A reliable method is presented for calculating the flowfield about a cascade of arbitrary two-dimensional airfoils. The method approximates the three-dimensional flow in a turbomachinery blade row by correcting for streamtube convergence and radius change in the throughflow direction. The method is a fully conservative solution of the full potential equation incorporating the finite volume technique on a body-fitted periodic mesh, with an artificial density imposed in the transonic region to ensure stability and the capture of shock waves. Comparison of results for several supercritical blades shows good agreement with their hodograph solutions. Other calculations for these profiles as well as standard NACA blade sections indicate that this is a useful scheme for analyzing both the design and off-design performance of turbomachinery blading.

Copyright © 1982 by ASME
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