TY - GEN
T1 - Fuel Spray and Operating Condition Impact on Ignition Performance in the ARC-M1 Combustor
AU - Wood, Eric J.
AU - Motily, Austen H.
AU - Trotter, Caleb J.
AU - Lee, Tonghun
AU - Mayhew, Eric K.
AU - Coburn, Vincent D.
AU - Temme, Jacob
AU - Kweon, Chol Bum
N1 - Funding Information:
Research was sponsored by the Army Research Laboratory and was accomplished under Cooperative Agreement Numbers W911NF-20-2-0220, W911NF-19-2-0239, and W911NF-18-2-0240 (ORAU Student Fellowship). The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the Army Research Laboratory or the U.S. Government. The U.S.
Funding Information:
This research was also funded by the U.S. Federal Aviation Administration Office of Environment and Energy through ASCENT, the FAA Center of Excellence for Alternative Jet Fuels and the Environment, project 65b Rapid Jet Fuel Prescreening through FAA Award Number DOT FAA 13-C-AJFE-UI 030 under the supervision of Anna Oldani. Any opinions, findings, conclusions, or recommendations expressed in this material are those of the authors and do not necessarily reflect the views of the FAA.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - In the interest of developing small-scale gas turbine combustors, understanding liquid fuel spray effects on global combustion ignition performance is critical. In these experiments, baseline ignition performance behavior is established for a relatively small-scale gas turbine combustor operating at cold-start and altitude ignition conditions. Additionally, ignition tests at cold-start conditions are conducted using multiple fuel spray nozzles to evaluate the effects of fuel spray behavior on global ignition probability performance. The combustor used for these experiments, the ARC-M1, was developed in conjunction with engine OEMs and replicates key geometric features of helicopter-size gas turbine combustors while offering convenient optical access. Baseline ignition performance measurements are conducted using an altitude chamber at near-sea level pressure (92.5 kPa) at three temperatures (15 °C,-10 °C, and-35 °C) and at altitude conditions corresponding to 10,000 ft elevation (69.4 kPa,-5 °C). Ignition measurements comparing fuel spray nozzles are conducted outside of the altitude chamber at cold-start inlet conditions (-5 °C & 25 °C, 103 kPa). Results demonstrate strong temperature and pressure effects on performance in the combustor, with both low temperature and low pressure conditions severely degrading performance. Comparisons between fuel nozzles show a major shift in the equivalence ratios that demonstrate ignition performance compared to the reference nozzle. The knowledge gained from this study will help direct gas turbine ignition modeling efforts and detailed experiments on this combustor investigating fuel spray effects on ignition performance and inform future small-scale combustor design.
AB - In the interest of developing small-scale gas turbine combustors, understanding liquid fuel spray effects on global combustion ignition performance is critical. In these experiments, baseline ignition performance behavior is established for a relatively small-scale gas turbine combustor operating at cold-start and altitude ignition conditions. Additionally, ignition tests at cold-start conditions are conducted using multiple fuel spray nozzles to evaluate the effects of fuel spray behavior on global ignition probability performance. The combustor used for these experiments, the ARC-M1, was developed in conjunction with engine OEMs and replicates key geometric features of helicopter-size gas turbine combustors while offering convenient optical access. Baseline ignition performance measurements are conducted using an altitude chamber at near-sea level pressure (92.5 kPa) at three temperatures (15 °C,-10 °C, and-35 °C) and at altitude conditions corresponding to 10,000 ft elevation (69.4 kPa,-5 °C). Ignition measurements comparing fuel spray nozzles are conducted outside of the altitude chamber at cold-start inlet conditions (-5 °C & 25 °C, 103 kPa). Results demonstrate strong temperature and pressure effects on performance in the combustor, with both low temperature and low pressure conditions severely degrading performance. Comparisons between fuel nozzles show a major shift in the equivalence ratios that demonstrate ignition performance compared to the reference nozzle. The knowledge gained from this study will help direct gas turbine ignition modeling efforts and detailed experiments on this combustor investigating fuel spray effects on ignition performance and inform future small-scale combustor design.
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U2 - 10.2514/6.2022-0364
DO - 10.2514/6.2022-0364
M3 - Conference contribution
AN - SCOPUS:85122965887
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -