Plasma assisted cavity flame ignition in supersonic flows

Do, Hyungrok; Cappelli, Mark A.; Mungal, M. G.

doi:10.1016/j.combustflame.2010.03.009

Cited by 148 publications

(43 citation statements)

References 19 publications

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“…Historically, these techniques have ranged from pure electrical energy addition via low-and highfrequency pulsed discharges [3,4] and plasma jets/ torches [5][6][7], to a combination of electrical and chemical energy addition via fueled torches. [8] While pure electrical energy addition is attractive because of its simplicity, it is conceivable that considerable electrical energy would be required.…”

Section: Introductionmentioning

confidence: 99%

Cavity ignition in supersonic flow by spark discharge and pulse detonation

Ombrello

Carter

Tam

et al. 2015

Proceedings of the Combustion Institute

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Ignition of an ethylene fueled cavity in a supersonic flow was achieved through the application of two energy deposition techniques: a spark discharge and pulse detonator (PD). High-frequency shadowgraph and chemiluminescence imaging showed that the spark discharge ignition was passive with the ignition kernel and ensuing flame propagation following the cavity flowfield. The PD produced a high-pressure and temperature exhaust that allowed for ignition at lower tunnel temperatures and pressures than the spark discharge, but also caused significant disruption to the cavity flowfield dynamics. Under certain cavity fueling conditions a multiple regime ignition process occurred with the PD that led to decreased cavity burning and at times cavity extinction. Simulations were performed of the PD ignition process, capturing the decreased cavity burning observed in the experiments. The PD exhaust initially ignited and burned the fuel within the cavity rapidly. Simultaneously, the momentary elevated pressure from the detonation caused a blockage of the cavity fuel, starving the cavity until the PD completely exhausted and the flowfield could recover. With sufficiently high cavity fueling, the decrease in burning during the PD ignition process could be mitigated. Cavity fuel injection and entrainment of fuel through the shear layer from upstream injection allowed for the spark discharge ignition process to exhibit similar behavior with peaks and valleys of heat release (but to a lesser extent). The results of using the two energy deposition techniques emphasized the importance of cavity fueling and flowfield dynamics for successful ignition. Published by Elsevier Inc. on behalf of The Combustion Institute.

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Section: Introductionmentioning

confidence: 99%

Cavity ignition in supersonic flow by spark discharge and pulse detonation

Ombrello

Carter

Tam

et al. 2015

Proceedings of the Combustion Institute

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“…These discharges have a high propensity to produce reactive radical species. The radical species in flammable mixtures facilitate combustion reactions to reduce the ignition delay time [19]. While nonequilibrium plasmas alone can be beneficial to flame stabilization, however, they are most often used in conjunction with wall features in supersonic flows to guarantee stable combustion.…”

Section: Introductionmentioning

confidence: 99%

Plasma assisted flame ignition of supersonic flows over a flat wall

Cappelli

et al. 2010

Combustion and Flame

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123

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“…Thus, it is of great importance to accelerate the combustion to ensure full heat release and stable combustion under such a hostile condition [2], especially at low Mach number flight condition, where ignition is the most critical problem for combustor design due to the low stagnation temperature [14,16]. To overcome the ignition difficulty in supersonic flow, application of both thermo-equilibrium and non-equilibrium plasma to supersonic combustion has become an active research field in recent years [5,11,13,22,27,30]. The plasma can not only facilitate the easy ignition of fuel/air mixture but also the acceleration of combustion process, which are crucial for the sustainability of stable combustion in supersonic free stream.…”

Section: Introductionmentioning

confidence: 99%

Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

Tong

et al. 2013

Aerospace Science and Technology

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By using a plasma jet (PJ) torch with 1.5 kW input power as an igniter, successful ignition for liquidkerosene fueled combustion experiment was conducted in a direct-connected supersonic test facility. The incoming flow has total temperature of 950 K and local Mach number of 1.8, corresponding to Mach 4 flight condition. In this study, several optical techniques, including high speed photography, high speed schlieren photography, and planar laser scattering (PLS) technique, were combined to study the ignition process, flame propagation, and mixing features of liquid kerosene fuel with air around the cavity. The effect of fuel injection position, injection pressure, and feedstock gas on ignition performance has been analyzed. The results indicate that local mixing is a critical factor for ignition. It is also shown that the PJ torch with N 2 + H 2 feedstock is superior to the PJ torch with N 2 feedstock for the ignition of liquidkerosene fuel. These results are valuable for the future optimization of kerosene-fueled scramjet engine when using a PJ torch as an igniter.

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Plasma assisted cavity flame ignition in supersonic flows

Cited by 148 publications

References 19 publications

Cavity ignition in supersonic flow by spark discharge and pulse detonation

Cavity ignition in supersonic flow by spark discharge and pulse detonation

Plasma assisted flame ignition of supersonic flows over a flat wall

Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

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