Active Stabilization of Axial Compressors With Circumferential Inlet Distortion

[+] Author and Article Information
C. M. van Schalkwyk

Scientific Systems Co., Inc., Woburn, MA 01801

J. D. Paduano, E. M. Greitzer, A. H. Epstein

Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 120(3), 431-439 (Jul 01, 1998) (9 pages) doi:10.1115/1.2841734 History: Received February 01, 1997; Online January 29, 2008


This paper describes the first experimental validation of transfer function modeling and active stabilization for axial compressors with circumferential inlet distortion. The inlet distortion experiments were carried out in a three-stage low-speed compressor. Theory–experiment comparisons of steady performance, unsteady stall precursor, and forced response (transfer function) data were all used to assess a control-theoretic version of the Hynes–Greitzer distorted flow model. The tests showed good agreement between theory and data and demonstrated that a priori predictions, based on geometry and steady-state performance data, can be used to design control laws that stabilize rotating stall with inlet distortion. Based on these results, active feedback control has been used to stabilize the inlet distortion induced instability associated with rotating stall onset. The stabilization allowed stall-free operation to be extended below the natural (distorted flow) stall point by up to 3.7 percent for a 0.8 dynamic head distortion. For a 1.9 dynamic head distortion, 40 percent of the mass flow range lost due to inlet distortion was regained through active control. The paper elucidates the difficulties associated with active control with distortion, and introduces a new control law that addresses many of these challenges.

Copyright © 1998 by The American Society of Mechanical Engineers
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