Low Aspect Ratio Transonic Rotors: Part 1—Baseline Design and Performance

[+] Author and Article Information
C. H. Law

Wright Laboratory, Wright-Patterson AFB, OH 45433

A. R. Wadia

GE Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 115(2), 218-225 (Apr 01, 1993) (8 pages) doi:10.1115/1.2929226 History: Received February 11, 1992; Online June 09, 2008


The analytical design and experimental test of a single-stage transonic axial-flow compressor are described. This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on compressor performance. The baseline design consisted of ruggedizing an existing compressor design that demonstrated outstanding aerodynamic performance, to correct some undesirable aeromechanical characteristics. The design study was performed by varying only one design parameter at a time, keeping the other design variables as close as possible to the baseline design. Specific design parameters of interest were those for which very few data were available to determine their sensitivity on compressor performance. This paper describes the baseline compressor design and its experimental performance. A detailed definition and flow analysis of the baseline design test point (used as the basis for all subsequent design variations) are provided.

Copyright © 1993 by The American Society of Mechanical Engineers
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