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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Online Combustor Stability Margin Assessment Using Dynamic Pressure Data

[+] Author and Article Information
Tim Lieuwen

School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA 30332-0150e-mail: tim.lieuwen@aerospace.gatech.edu

J. Eng. Gas Turbines Power 127(3), 478-482 (Jun 24, 2005) (5 pages) doi:10.1115/1.1850493 History: Received October 01, 2003; Revised March 01, 2004; Online June 24, 2005
Copyright © 2005 by ASME
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References

Figures

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Variation of dynamic pressure amplitude in combustor with premixer velocity
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Dependence of autocorrelation of raw acoustic pressure data measured under stable (top, u=27 m/s) and unstable (bottom, u=21 m/s) conditions
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Time dependence of the autocorrelation, Ci(t), (○) and Hilbert transform of the autocorrelation (−). Raw data bandpass filtered about the 630 Hz mode with a fourth-orderButterworth filter, with a bandwidth set to 10% of the center frequency (u=33.9 m/s).
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Dependence of damping estimate, ζ, upon bandpass filter width (fcenter=630 Hz,u=21.9 m/s; four cycles of data were used for an estimate)
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Fourier transform of combustor pressure (u=25.9 m/s)
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Dependence of 430 (□) and 630 (*) Hz mode amplitude upon premixer velocity
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Dependence of 430 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity
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Dependence of 630 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity
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Dependence of 285 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity
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Dependence of 730 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity
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Dependence of 570 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity
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Dependence of 132 Hz mode pressure amplitude (▪) and damping coefficient (○) upon premixer velocity

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