Twin-swirler is used as a major form in aero-engine combustor dome to make a recirculation zone. The effects of the swirl number of the second stage radial swirler on ignition and combustion stability performance were mainly studied. The numerical simulation results were validated well with the design parameters of the second stage radial swirler. Experimental studies show that the swirl number of the second stage radial swirler has no effect on the combustor ignition performance. However

the decrease of this swirl number will obviously improve the lean blow-out performance. The entrainment effect of swirl would impact the flame stabilization in the recirculation zone. Decreasing swirl number of the second stage radial swirler can increase the downstream entrainment and optimize the matching between the flow and flame in the recirculation zone

and this is more beneficial to improve the combustion stability.