Numerical study on the transient ignition characteristics of multi-swirl combustor enhanced by gliding arc plasma

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Abstract
Against the background of demanding ignition stability requirements for high-temperature-rise aero-engine combustors, this paper numerically explores transient ignition and flame evolution in a gliding arc plasma-assisted multi-swirl combustor via a 3D two-phase URANS turbulent combustion approach. It employs the realizable k-ε, eddy dissipation concept, and discrete phase models alongside a self-built gliding arc trajectory and thermal-reaction coupling model to reproduce the full process of arc discharge, initial flame kernel generation, flame propagation, and self-sustained combustion. Results show that gliding arc plasma deposits energy and momentum to regulate local flow structure, fuel atomization, and active species generation including O and OH radicals. The initial flame kernel forms at 6.4 ms dominated by plasma-induced radical reactions and optimal local equivalence ratio. A newly defined heat release-dissipation Damköhler number (Da_hd) is proposed as a criterion for flame stability: Da_hd > 1 enables self-sustained flame propagation while Da_hd < 1 leads to flame extinction due to dominant turbulent dissipation. The intermediate recirculation zone and low-velocity zone provide favorable low-turbulence environments for flame anchoring. Eventually, the flame evolves into a stable V-shaped global propagation structure under the synergistic effect of plasma periodic energy supplementation, flow recirculation, and turbulent mixing. This paper reveals the multi-field coupling mechanism of plasma-flow-chemistry and provides a theoretical basis for the application of gliding arc plasma in aero-engine combustor ignition enhancement.

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