Development of plasma actuators for re-ignition of aeroengine under high altitude conditions

Abstract Re-ignition of aeroengine under high altitude conditions is great importance to the safety and use lean-burn engines. The present work investigated experimental numerical analysis flow re-ignition characteristics in a rectangular burner. A ring-needle type plasma actuator was developed powered by voltage nanopulsed generator with different percentage values amplitude frequencies. Flow visualizations using speed camera Proper Orthogonal Decomposition (POD) were performed recognize dominant structures. Experimental results showed transport effects such as induced an impact on recirculation zone near corners combustor, improving mixing performance, which could be contribute reduction ignition delay timings. characterization non-reactive allowed estimation electrical power optimal reduced electric field (EN) value, then used input study for flame analysis. Ignition analyzed coupling two tools ZDPlasKin Chemkin. It noticed that time required achieve maximum temperature actuation significantly compared autoignition timings (clean case). Maximum observed at inlet pressure 1 bar (3.5×10 -5 s) respect clean case (1.1×10 -3 s). However, reduced, increased. At 0.6 occurred 0.0048s 0.0022s case, respectively.