Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 2—Computational Assessment

[+] Author and Article Information
K. L. Gundy-Burlet, M. M. Rai

NASA Ames Research Center, Moffett Field, CA 94035-1000

R. C. Stauter, R. P. Dring

United Technologies Research Center, East Hartford, CT 06108

J. Turbomach 113(2), 227-232 (Apr 01, 1991) (6 pages) doi:10.1115/1.2929090 History: Received January 01, 1990; Online June 09, 2008


Fluid dynamics of turbomachines are complicated because of aerodynamic interactions between rotors and stators. It is necessary to understand the aerodynamics associated with these interactions in order to design turbomachines that are both light and compact as well as reliable and efficient. The current study uses an unsteady, thin-layer Navier–Stokes zonal approach to investigate the unsteady aerodynamics of a multistage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results have been computed for a 2 1/2-stage compressor configuration. The numerical data compare well with experimental data for surface pressures and wakes. In addition, the effect of grid refinement on the solution is studied.

Copyright © 1991 by The American Society of Mechanical Engineers
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