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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuel

Determination of Thermoacoustic Response in a Demonstrator Gas Turbine Engine

[+] Author and Article Information
C. A. Arana, B. Sekar

Propulsion Directorate, Air Force Research Laboratory, Wright Patterson AFB, OH 45433-7251

M. A. Mawid

Engineering Research & Analysis Company, Dayton, OH 45440-4429

C. B. Graves

Pratt and Whitney, East Hartford, CT

J. Eng. Gas Turbines Power 124(1), 46-57 (Oct 01, 2000) (12 pages) doi:10.1115/1.1374200 History: Received October 01, 1999; Revised October 01, 2000
Copyright © 2002 by ASME
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References

Figures

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Schematic of the baseline fuel injector design configuration A
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Schematic of new fuel injector, design configuration B
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Front-end cross section of the base combustor configuration
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Waterfall graphs for pressure fluctuations for fuel injector configuration A
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Waterfall graphs for pressure fluctuations for fuel injector configuration B
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Waterfall for pressure fluctuations for fuel injector configuration B
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Frequency versus pressure drop
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Ratio of the fluctuating upstream pressure for downstream velocity (transfer function)
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Phase relationship for ratio of upstream pressure to downstream velocity
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Ratio of the fluctuating upstream pressure to downstream velocity for design configuration B
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Ratio of the fluctuating upstream pressure to downstream velocity for design configurations A and B
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Schematic of the combustion rig
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(a) and (b) Measured spectral density (PSD) versus frequency
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(a) and (b) Measured transfer function
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(a) and (b) Measured transfer function versus frequency with LING excitation
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Schematic swirler and inner passage of fuel injector as a lumped sum
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Predicted fuel injector lumped-system response factor
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Predicted fuel injector reactance as a function of frequency
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Predicted fuel injector response factor versus frequency
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Predicted magnitude of the imaginary part of the fuel injector transfer function versus frequency

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