Abstract
The ignition of kerosene spray in an aero-engine combustor is complex due to the fuel injection, mixing, and swirl flow. To explore the influence of ignition position on the ignition characteristics of the aero-engine combustor, a three-sector rich-quench-lean (RQL) combustor experiment system was designed. The experimental study on the ignition process of different ignition positions was carried out. Two different positions of igniter, located respectively in the left liner and middle liner, were considered. Experimental results show that observations revealed a consistent ignition propagation pattern across various axial cross-sections, demonstrating distinct roles for combustor structures, such as the outer recirculation zone (ORZ), recirculation vortex, and inner recirculation zone (IRZ) during the process. The upper recirculation vortex and ORZ create favorable conditions for flame kernel formation, which then spreads to ignite the IRZ and lower recirculation vortex, aiding primarily in heat transfer, before propagating downstream to light up additional vortex structures. Furthermore, the ignition position significantly influences the flame development in two schemes, showing variations in flame intensity under different equivalence ratios and resulting in divergent propagation states. Additionally, during circumferential ignition, variances in ignition positions and flow field structures elongate the flame path for the middle ignition scheme, introducing both reverse and co-rotating motions between flame and airflow. This interaction accelerates the clockwise flame front propagation while simultaneously damping the counterclockwise movement, showcasing the complex dynamics of flame behavior in response to ignition and flow field variations.
Published Version
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