Prediction of Compressor Cascade Performance Using a Navier–Stokes Technique

[+] Author and Article Information
R. L. Davis

Computational Fluid Dynamics Group, United Technologies Research Center, East Hartford, CT 06108

D. E. Hobbs, H. D. Weingold

Fan and Compressor Technology Group, Pratt and Whitney, East Hartford, CT 06108

J. Turbomach 110(4), 520-531 (Oct 01, 1988) (12 pages) doi:10.1115/1.3262226 History: Received December 15, 1987; Online November 09, 2009


An explicit, time marching, multiple-grid Navier–Stokes technique is demonstrated for the prediction of quasi-three-dimensional turbomachinery compressor cascade performance over the entire incidence range. A numerical investigation has been performed in which the present Navier–Stokes procedure was used to analyze a series of compressor cascade viscous flows for which corresponding experimental data are available. Results from these calculations show that the current viscous flow procedure is capable of predicting cascade profile loss and airfoil pressure distributions with high accuracy. The results from this numerical investigation in the form of comparisons between the predicted profile loss, exit gas angle, and pressure distributions with experimental data are presented in this paper. Results from a grid refinement study are also shown to demonstrate that the Navier–Stokes solutions are grid independent.

Copyright © 1988 by ASME
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