TY - GEN
T1 - Laser-induced plasma ignition experiments in a direct-connect supersonic combustor at Mach 3
AU - Baccarella, Damiano
AU - Lee, Gyu Sub
AU - Liu, Qili
AU - Elliott, Gregory S.
AU - Freund, Jonathan B.
AU - Lee, Tonghun
N1 - Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - A new direct-connect supersonic combustor has been designed and tested for studies (and corresponding simulation-based predictions) of laser-induced ignition. The new combustor will interface with the ACT-II supersonic combustion tunnel to perform studies on plasma-assisted ignition in an ethylene-fueled supersonic flow. This paper described the combustor design and geometry, the flow characteristics and initial experimental results. The supersonic combustor includes a cavity flame-holder, where ethylene fuel is injected, mixed with entrained air, and ignited. Two injector configurations are included, one horizontal and one vertical, directed in such a way to enhance the cavity flow recirculation. Two different plasma ignition mechanisms were considered, 1) a laser induced plasma (LIP) located at the center of the cavity and 2) a spark plug placed on the bottom surface of the cavity. The diagnostics tools tested to characterize the flow include time-resolved pressure measurements, high-speed schlieren visualization and OH* chemiluminescence visualization, and instantaneous planar laser induced fluorescence (PLIF) of the CH radical.
AB - A new direct-connect supersonic combustor has been designed and tested for studies (and corresponding simulation-based predictions) of laser-induced ignition. The new combustor will interface with the ACT-II supersonic combustion tunnel to perform studies on plasma-assisted ignition in an ethylene-fueled supersonic flow. This paper described the combustor design and geometry, the flow characteristics and initial experimental results. The supersonic combustor includes a cavity flame-holder, where ethylene fuel is injected, mixed with entrained air, and ignited. Two injector configurations are included, one horizontal and one vertical, directed in such a way to enhance the cavity flow recirculation. Two different plasma ignition mechanisms were considered, 1) a laser induced plasma (LIP) located at the center of the cavity and 2) a spark plug placed on the bottom surface of the cavity. The diagnostics tools tested to characterize the flow include time-resolved pressure measurements, high-speed schlieren visualization and OH* chemiluminescence visualization, and instantaneous planar laser induced fluorescence (PLIF) of the CH radical.
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U2 - 10.2514/6.2019-3926
DO - 10.2514/6.2019-3926
M3 - Conference contribution
AN - SCOPUS:85095963008
SN - 9781624105906
T3 - AIAA Propulsion and Energy Forum and Exposition, 2019
BT - AIAA Propulsion and Energy Forum and Exposition, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum and Exposition, 2019
Y2 - 19 August 2019 through 22 August 2019
ER -