The flame structure and the limits of operation of a lean premixed swirl flame were experimentally investigated under piloted and nonpiloted conditions. Flame stabilization and blow out limits are discussed with respect to pilot fuel injection and combustor liner cooling for lean operating conditions. Two distinctly different flow patterns are found to develop depending on piloting and liner cooling parameters. These flow patterns are characterized with respect to flame stability, blow out limits, combustion noise, and emissions. The combustion system explored consists of a single burner similar to the burners used in Siemens annular combustion systems. The burner feeds a distinctively nonadiabatic combustion chamber operated with natural gas under atmospheric pressure. Liner cooling is mimicked by purely convective cooling and an additional flow of “leakage air” injected into the combustion chamber. Both additional air flow and the pilot fuel ratio were found to have a strong influence on the flow structure and stability of the flame close to the lean blow off (LBO) limit. It is shown by laser Doppler velocimetry that the angle of the swirl cone is strongly affected by pilot fuel injection. Two distinct types of flow patterns are observed close to LBO in this large scale setup: While nonpiloted flames exhibit tight cone angles and small inner recirculation zones (IRZs), sufficient piloting results in a wide cone angle and a large IRZ. Only in the latter case, the main flow becomes attached to the combustor liner. Flame structures deduced from flow fields and CH-chemiluminescence images depend on both the pilot fuel injection and liner cooling.
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September 2010
Research Papers
Effects of Pilot Fuel and Liner Cooling on the Flame Structure in a Full Scale Swirl-Stabilized Combustion Setup
Jens Färber,
Jens Färber
Institut für Thermische Strömungsmaschinen,
e-mail: jens.faerber@kit.edu
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germany
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Rainer Koch,
Rainer Koch
Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germany
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Hans-Jörg Bauer,
Hans-Jörg Bauer
Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germany
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Matthias Hase,
Matthias Hase
SIEMENS AG Energy Sector
, Mellinghofer Str. 55, 45466 Mülheim an der Ruhr, Germany
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Werner Krebs
Werner Krebs
SIEMENS AG Energy Sector
, Mellinghofer Str. 55, 45466 Mülheim an der Ruhr, Germany
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Jens Färber
Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germanye-mail: jens.faerber@kit.edu
Rainer Koch
Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germany
Hans-Jörg Bauer
Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology—KIT
, Kaiserstr. 12, 76128 Karlsruhe, Germany
Matthias Hase
SIEMENS AG Energy Sector
, Mellinghofer Str. 55, 45466 Mülheim an der Ruhr, Germany
Werner Krebs
SIEMENS AG Energy Sector
, Mellinghofer Str. 55, 45466 Mülheim an der Ruhr, GermanyJ. Eng. Gas Turbines Power. Sep 2010, 132(9): 091501 (7 pages)
Published Online: June 10, 2010
Article history
Received:
April 6, 2009
Revised:
October 19, 2009
Online:
June 10, 2010
Published:
June 10, 2010
Citation
Färber, J., Koch, R., Bauer, H., Hase, M., and Krebs, W. (June 10, 2010). "Effects of Pilot Fuel and Liner Cooling on the Flame Structure in a Full Scale Swirl-Stabilized Combustion Setup." ASME. J. Eng. Gas Turbines Power. September 2010; 132(9): 091501. https://doi.org/10.1115/1.4000588
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