Three-Dimensional Flow Phenomena in a Transonic, High-Throughflow, Axial-Flow Compressor Stage

[+] Author and Article Information
W. W. Copenhaver, S. L. Puterbaugh

Wright Laboratory, Wright-Patterson AFB, OH 45433

C. Hah

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 115(2), 240-248 (Apr 01, 1993) (9 pages) doi:10.1115/1.2929228 History: Received February 11, 1992; Online June 09, 2008


A detailed aerodynamic study of a transonic, high-throughflow, single-stage compressor is presented. The compressor stage was comprised of a low-aspect-ratio rotor combined alternately with two different stator designs. Both experimental and numerical studies are conducted to understand the details of the complex flow field present in this stage. Aerodynamic measurements using high-frequency, Kulite pressure transducers and conventional probes are compared with results from a three-dimensional viscous flow analysis. A steady multiple blade row approach is used in the numerical technique to examine the detailed flow structure inside the rotor and the stator passages. The comparisons indicate that many flow field features are correctly captured by viscous flow analysis, and therefore unmeasured phenomena can be studied with some level of confidence.

Copyright © 1993 by The American Society of Mechanical Engineers
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