Thermal Release Characteristics of Aeroengine Combustor Outlet Modulated by Gliding Arc Plasma

Abstract A gliding arc plasma (GAP) combustion dome is used to construct a diagnostic platform for the swirl combustor of aeroengines. Thermocouple measurements, particle image velocimetry, and spontaneous emission imaging are employed to measure the outlet temperature field, combustor flow field, and combustion field information. The influence of GAP‐assisted combustion on the outlet temperature profile of the combustor is then analyzed. The results demonstrate that gliding arc discharge allows the flame to reside closer to the combustion dome, shifting the combustion reaction zone forward. This combustion zone contains most of the active particles generated by gliding arc discharge, enabling a more complete combustion reaction and better heat release. The forward movement of the combustion reaction zone also provides sufficient space for flames to develop inside the combustor. The thermal and transport effects of gliding arc discharge enhance the aerodynamic effect inside the combustor, improve fuel atomization, broaden the flame development range inside the combustor, and make the combustion reaction more complete. Under various working conditions, the application of GAP‐assisted combustion increases combustion efficiency by 10.3%, the outlet temperature of the combustor rises by 141.6°C, the outlet temperature distribution function decreases by 29.56%, and the hot‐streak area ratio decreases by 72.6%.