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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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References

Appelton, J. P., and Heywood, J. B., 1972, “The Effects of Imperfect Fuel-Air Mixing in a Burner on NO Formation From Nitrogen in the Air and the Fuel,” 14th International Symp. on Combustion, pp. 777–786.
Lyons,  V. J., 1982, “Fuel/Air Non-uniformity Effects on Nitric Oxide Emissions,” AIAA J., 20, pp. 660–665.
Cowell, L. H., Rajput, A., and Rawlins, D. C., 1996, “Development of a Dual-Fuel Injection System For Lean Premixed Industrial Gas Turbines,” ASME Paper 96-GT-195.
Smith, K. O., and Cowell, L. H., 1989, “Experimental Evaluation of Liquid-Fueled, Lean-Premixed Gas Turbine Combustor,” ASME Paper 89-GT-264.
McVey, J. B., and Kennedy, J. B., 1980, “Lean Stability Augmentation Study,” J. Energy, 4 .
Snyder, S. S., Rosfjord, T. J., McVey, J. B., and Chiappetta, L. M., 1994, “Comparison of Fuel/Air Mixing and NOx Emissions for Tangential Entry Nozzle, ASME Paper 94-GT-283.
Richards,  G. A., and Janus,  M. C., 1998, “Characterization of Oscillations During Premix Gas Turbine Combustion,” ASME J. Eng. Gas Turbines Power, 120, No. 2, pp. 294–302.
Straub, D. L., and Richards, G. A., 1998, “Effect of Fuel Nozzle Configuration on Premix Combustion Dynamics,” ASME Paper 98-GT-492.
Lieuwen, T., and Zinn, B. T., 1998, “Theoretical Investigation of Combustion Instability mechanisms in Lean Premixed Gas Turbines,” AIAA Paper 98-0641.
Putnam, A. A., 1971, Combustion Driven Oscillations in Industry, Elsevier, New York.
Straub, D. L., and Richards, G. A., 1999, “Effect of Axial Swirl-Vane Location On Combustion Dynamics,” ASME Paper 99-GT-109.
Mahan, J. R., and Karchmer, A., 1991, “Combustion Core Noise,” Aeroacoustics of Flight Vehicles: Theory and Practice, Vol. 1: Noise Sources, NASA Langley Research Center, available from AIAA Technical Library.
Gulder,  O. L., 1986, “Flame Temperature Estimation of Conventional and Future Jet Fuels,” ASME J. Eng. Gas Turbines Power, 108, pp. 376–380.

Figures

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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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