Abstract: International audience ; This work presents an experimental study of a gas turbine model combustor stabilized by Nanosecond Repetitively Pulsed (NRP) discharges. The combustor consists of a plenum, a burner, and a combustion chamber with a square section. The injection device, inspired by Lean Premixed technologies, is composed of two stages (pilot and multipoint), both stabilized by swirl. The combustor is operated at atmospheric pressure with air and methane at a flame thermal power of 50 kW, and the power ratio between the stages is varied in this study. The Lean Blow-Out limit is extended using NRP discharges, and the plasma stabilization is enhanced by optimizing the position of the electrode. Three electrode positions are tested: in the pilot stage, in the multipoint stage and in the chamber backplane. The strongest plasma effect at all staging ratios is obtained for the "multipoint position".
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