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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuel

Passive Control of Combustion Instability in Lean Premixed Combustors

[+] Author and Article Information
Robert C. Steele, Luke H. Cowell

Solar Turbines Inc., San Diego, CA 92186-5376

Steven M. Cannon, Clifford E. Smith

CFD Research Corporation, Huntsville, AL 35805

J. Eng. Gas Turbines Power 122(3), 412-419 (May 15, 2000) (8 pages) doi:10.1115/1.1287166 History: Received March 09, 1999; Revised May 15, 2000
Copyright © 2000 by ASME
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References

Roberts, P. B., Kubasco, A. J., and Sekas, N. T., 1981, “Development of a Low NOx Lean Premixed Annular Combustor,” ASME paper 81-GT-40.
Smith, K. O., Angello, L. C., and Kurzynske, F. R., 1986, “Design and Testing of an Ultra-Low NOx Gas Turbine Combustor,” ASME paper 86-GT-263.
Rayleigh, J. S., 1878, “The Explanation of Certain Acoustical Phenomena,” Royal Institute Proceedings, VIII , pp. 536–542.
Richards, G. A., and Janus, M. C., 1997, “Characterization of Oscillations During Premix Gas Turbine Combustion,” ASME Paper 97-GT-244.
Lieuwen, T., and Zinn, B. T., 1998, “The Role of Equivalence Ratio Oscillations in Driving Combustion Instabilities in Low NOx Gas Turbines,” presented at the 27th International Symposium on Combustion, Boulder, CO, August.
Rawlins, D. C., 1995, “Dry Low Emissions: Improvements to the SoLoNOx Combustion System,” Eleventh Symposium on Industrial Applications of Gas Turbines Canadian Gas Association, Banff, Alberta, Canada, October.
Etheridge, C. J., 1994, “Mars SoLoNOx—Lean Premix Combustion Technology in Production,” ASME Paper 94-GT-255, The Hague.
Paschereit, C. O., and Polifke, W., 1998, “Investigation of the Thermoacoustic Characteristics of a Lean Premixed Gas Turbine Burner,” ASME Paper 98-GT-582.
Peracchio, A. A., and Proscia, W. M., 1998, “Nonlinear Heat-Release Acoustic Model for Thermoacoustic Instability in Lean Premixed Combustors,” ASME Paper 98-GT-269.
Smith, C. E., and Leonard, A. D., 1997, “CFD Modeling of Combustion Instability in Premixed Symmetric Combustors,” ASME Paper 97-GT-305.
Cannon, S. M., and Smith, C. E., 1998, “Numerical Modeling of Combustion Dynamics in a Lean Premixed Combustor,” FACT-Vol. 22, 1998 International Joint Power Generation Conference.
Richards,  G. A., Gemmen,  R. S., and Yip,  M. J., 1997, “A Test Device for Premixed Gas Turbine Combustion Oscillations,” ASME J. Eng. Gas Turbines Power, 119, pp. 776.
Putnam, A. A., 1971, Combustion Driven Oscillations in Industry, American Elsevier Publishers, New York, NY.
Yahkot,  V., Orszag,  S. A., Thangam,  S., Gatski,  T. B., and Speziale,  C. G., 1992, “Development of Turbulent Models for Shear Flows by a Double-Expansion Technique,” Phys. Fluids, 4, pp. 1510–1520.
Spring, S. A., Smith, C. E., and Leonard, A. D., 1995, “Advanced Demonstration of Fuel Injector/Flameholder for High Speed Ramburners,” WL-TR-95-2068, CFDRC Report No. 4166/2.
Westbrook,  C. K., and Dryer,  F. L., 1981, “Simplified Reaction Mechanisms for the Oxidation of Hydrocarbon Fuels in Flames,” Combust. Sci. Technol., 27, pp. 31–43.
Malte, P. C., and Nicol, D. G., 1996, “Development of a Five-Step Global Mechanism for Methane Oxidation and NO Formation,” final report to Applied Science and Engineering Technologies and Solar Turbines, University of Washington, Seattle, WA, June 12, 1996.
Janus, M. C., Richards, G. A., Yip, M. J., and Robey, E. H., 1997, “Effects of Ambient Conditions and Fuel Composition on Combustion Stability,” ASME Paper 97-GT-266.

Figures

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Effects of pilot fuel on combustor pressure oscillations and NOx emissions
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Fuel injector modifications to eliminate combustor oscillations
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Basic research injector design
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Cutaway view of FETC test combustor 12
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The stable and unstable regions of τ*F taken from injector tests
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Calculation domain for CFD analysis
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Comparison of predicted velocity distributions in the three-dimensional and calibrated two-dimensional premixer models
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Comparison of heat release using the one-step to equilibrium products and the five-step chemical reaction models
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Predicted mean fluid traces for different fuel injection locations
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Predicted limit cycle pressure history at combustor mid-section [fuel location=5.8 cm (2.29 in)]
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Predicted heat release contours during a complete cycle [fuel location=5.8 cm (2.29 in)]
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Time history of pressure at combustor mid-section for fuel injection locations of (a) 4.3 cm [1.69 in], (b) 4.6 cm [1.81 in], (c) 4.9 cm [1.93 in], (d) 5.8 cm [2.29 in], (e) 6.7 cm [2.65 in], (f) 7.6 cm [3.0 in], (g) 7.9 cm [3.12 in], and (h) 8.5 cm [3.36 in]
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Comparison of measured and predicted instability results as a function of fuel injection location

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