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TECHNICAL PAPERS

Tailored Structural Design and Aeromechanical Control of Axial Compressor Stall—Part II: Evaluation of Approaches

[+] Author and Article Information
L. G. Fréchette

Department of Mechanical Engineering, Columbia University, New York, NY 10027

O. G. McGee

Department of Civil, Environmental Engineering, and Geodetic Science, The Ohio State University, Columbus, OH 43210

M. B. Graf

Mars and Company, 124 Mason Street, Greenwich, CT 06830

J. Turbomach 126(1), 63-72 (Mar 26, 2004) (10 pages) doi:10.1115/1.1644556 History: Received December 01, 2002; Revised March 01, 2003; Online March 26, 2004
Copyright © 2004 by ASME
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References

Figures

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Illustration of aeromechanical feedback schemes
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Compressor characteristics used in this study: (a) MIT single stage (Gysling and Greitzer 2), (b) MIT three-stage (Haynes et al. 3)
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Root locus plots showing the growth rates and rotation rates of the first and second harmonic modes in the MIT 1-stage and 3-stage compressors. Results are shown for cases with and without aeromechanical feedback scheme #1, using the models with and without aerodynamic lags. Flow coefficient values decrease from 0.6 to 0.3 by increments of 0.03, with the eigenvalues at the stalling flow coefficient identified by the plus sign.
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Structural control parameters for maximum stable range extension. Optimal structural frequency, Q, and damping ratio, ζ are shown for the various aeromechanical schemes. Results are presented for the MIT 1-stage and 3-stage compressors, modeling the aerodynamic blade row response with and without time lags for loss and deviation (solid and dashed lines respectively).
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Pressure rise characteristics and slope for the MIT 1-stage and 3-stage compressors. Stall points with the various aeromechanical feedback schemes are identified, as well as the stall points for the baseline compressors with and without loss and deviation lag dynamics.
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Flow range extension and the corresponding maximum achievable slope for the MIT 1-stage and 3-stage compressors with the various aeromechanical feedback schemes (flow range is defined as the difference in stalling flow coefficient between the aeromechanical (close-loop) and baseline (open-loop) compression systems
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Aeromechanical modal damping represented by the closed-loop growth rates of the first and second harmonic main fluid modes in the MIT 1-stage and 3-stage compressors. Results shown at the stall point for each optimized aeromechanical scheme using the present models with and without aerodynamic lags.
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True control authority of the various aeromechanical schemes, based on the limiting harmonic at the neutral stability for each optimized aeromechanical scheme
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Ideal control authority of the various aeromechanical schemes, based on the limiting harmonic at the neutral stability for each optimized aeromechanical scheme

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