| Citation: | ZHOU Yu, HUANG Yuan, CHEN Weiqiang, et al. Numerical simulation of gliding arc ignition characteristics in aeroengine combustor[J]. Journal of Aerospace Power, 2025, 40（5）：20230697 doi: 10.13224/j.cnki.jasp.20230697
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To gain an improved understanding of the ignition characteristics in real aeroengine combustor with gliding arc, a modeling and numerical simulation method of the gliding arc was developed on the CFD platform GTCC and tested on a model combustor with single stage swirler. Numerical simulation of the ignition by gliding arc in real combustor with two-stage axial swirler was carried out under 6 km high-altitude inflow condition. Simulation results showed that the gliding arc on fixed track can significantly enhance the performance of fuel pulverization and ignition, induce periodically anchored flame around the swirler outlet with the fuel-air-ratio, arc radius and rotating speed equal to 0.015, 1.5 mm and 100（°）/ms, respectively. The overall flow field approached the critical status of catching fire and eventually ignited with the arc radius increasing to 2.0 mm. Afterwards, fuel-air-ratio was reduced to 0.01 and the ignition processes with arc radius of 2.0 mm and 2.5 mm were simulated. Mean gaseous kerosene proportion on the outlet of swirler increased from 8.11% to 22.70% with stronger actuation, which successfully impelled the anchored flame to break through the critical ignition limit. Compared with the fuel-air-ratio limit
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