Active Stabilization of Rotating Stall in a Three-Stage Axial Compressor

[+] Author and Article Information
J. M. Haynes, G. J. Hendricks, A. H. Epstein

Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 116(2), 226-239 (Apr 01, 1994) (14 pages) doi:10.1115/1.2928357 History: Received March 17, 1993; Online June 09, 2008


A three-stage, low-speed axial research compressor has been actively stabilized by damping low-amplitude circumferentially traveling waves, which can grow into rotating stall. Using a circumferential array of hot-wire sensors, and an array of highspeed individually positioned control vanes as the actuator, the first and second spatial harmonics of the compressor were stabilized down to a characteristic slope of 0.9, yielding an 8 percent increase in operating flow range. Stabilization of the third spatial harmonic did not alter the stalling flow coefficient. The actuators were also used open loop to determine the forced response behavior of the compressor. A system identification procedure applied to the forced response data then yielded the compressor transfer function. The Moore-Greitzer two-dimensional stability model was modified as suggested by the measurements to include the effect of blade row time lags on the compressor dynamics. This modified Moore-Greitzer model was then used to predict both the open and closed-loop dynamic response of the compressor. The model predictions agreed closely with the experimental results. In particular, the model predicted both the mass flow at stall without control and the design parameters needed by, and the range extension realized from, active control.

Copyright © 1994 by The American Society of Mechanical Engineers
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