TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Application of Macrolamination Technology to Lean, Premixed Combustion

[+] Author and Article Information
A. Mansour, M. Benjamin

Parker Hannifin Corporation Gas Turbine Fuel Systems Division Mentor, OH 44060

D. L. Straub, G. A. Richards

U.S. Department of Energy, National Energy Technology Lab, Morgantown, WV 26505

J. Eng. Gas Turbines Power 123(4), 796-802 (Oct 01, 2000) (7 pages) doi:10.1115/1.1378296 History: Received October 01, 1999; Revised October 01, 2000
Copyright © 2001 by ASME
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Cross section of Parker-Hannifin premixer
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Schematic of experimental NETL combustor
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Approach to calculate fuel residence time
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Range of fuel transport times
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Pollutant emissions for all nozzle configurations and all operating conditions (50<U<80 m/s,0.55<ϕ<0.75, 5 atm, 533 K)
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NOx emissions as a function of nozzle configuration and adiabatic flame temperature (DF-2 fuel). No pilot fuel is used, so leaner conditions are not investigated.
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Nox/RMS pressure level (percent of ambient) relationship (Case A, 80 m/s, DF-2 fuel)
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Stability maps for each nozzle configuration and fuel type
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Time lag model description of the experimental results. Both fuel types can be described by a simple time lag.
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Dominant frequencies observed as a function of velocity for two equivalence ratio conditions (Case B on DF-2 fuel). Constant values of (transport time)* (frequency) are also shown.




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