In the present article, the effects of stabilization air temperature and mass flow rate as well as stabilization air swirl intensity on the combustion characteristics of liquid diesel fuel ( \(\:{C}_{10}{H}_{22}\) ) are analyzed. The cylindrical model combustion chamber consists of four stabilizing jets. Evaporation of the fuel spray is simulated using the discrete phase model based on the Eulerian-Lagrangian approach. The unsteady turbulent flow is modeled using the Reynolds stress model. Radiative heat transfer and combustion processes are modeled using the discrete ordinates model and the laminar flamelet model, respectively. Concentrations of \(\:\text{N}\text{O}\) species are determined through post-processing. Simulation results are validated against experimental data, showing strong agreement in temperature and \(\:\text{N}\text{O}\) distributions. Present findings reveal that a progressive elevation of the stabilization air temperature from \(\:295\:\text{K}\) to \(\:445\:\text{K}\) yields a roughly 6.5% increment in the axial total temperature of the mixture at the outlet of the combustor. An increase in the stabilization air temperature enhances the rate of \(\:\text{N}\text{O}\) production, whereas an augmentation of stabilization air mass flow rate weakens it. Implementing a swirler at the stabilizing air jet inlet results in a remarkable reduction in the concentration of \(\:\text{N}\text{O}\) . Particularly, changing swirler vane angle to \(\:5^\circ\:\) , \(\:10^\circ\:\) , and \(\:15^\circ\:\) induces a decrease in the concentration of \(\:\text{N}\text{O}\) at the center of combustor exit by almost 74.3%, 60.3%, and 56.6%, respectively. The findings provide practical insights for reducing emissions in jet-stabilized combustion systems.
