Liquid atomization is a very complex issue, involving multiple length and time scales over several orders of magnitude. To better understand the atomization characteristics of the main injection in a lean premix prevaporize (LPP) combustor, a volume of fluid (VOF)–particle conversion algorithm Lagrangian particle tracking (LPT) coupled approach was proposed to simultaneously reproduce the primary and secondary breakup processes. A VOF model with an adaptive mesh refinement strategy was used to resolve the liquid disintegration on a large scale. The small liquid structures qualified as droplets were transformed into discrete particles based on particle conversion criteria. Next, these particles were tracked using the LPT method to simulate the secondary breakup process. The proposed coupled method used in the Eulerian/Lagrangian framework was validated against liquid jet in crossflow experimental data. The numerical results achieved good agreement with the experimental data. Finally, the proposed method was used to predict the atomization characteristics of the main injection in an LPP combustor under various aerodynamic conditions. Qualitative and quantitative information about liquid deformation and spray characteristics were obtained, which varied depending on the aerodynamic parameters.

The impact of the swirl number on the flow field of a single-stage swirl combustor is investigated using the particle image velocimetry technology. The variations in recirculation zone size, pulsating region, turbulent distribution, vorticity, and Reynolds stress within the combustor are summarized through quantitative analysis of the flow field. Experimental results indicate the following: (1) Under the same air mass flow rate, the length of the recirculation zone in the combustion state is shorter than that in the cold state. (2) The length of the recirculation zone and the axial vortex spacing display a decreasing trend as the swirl number increases, while the width of the recirculation zone demonstrates an increasing trend. (3) For the single-stage swirl combustor, the primary pulsating region is at the swirling jet area at the exit of the swirl. As the swirl number increases, the standard deviation of radial velocity fluctuations and turbulent kinetic energy also increase. (4) The strong shear region of the single-stage swirl combustor can be divided into inner and outer shear layers based on the vorticity distribution and the Q criterion. The vortices in the inner and outer shear layers exhibit opposite orientations according to the vorticity distribution. Overall, the research results can provide basic experimental data for numerical simulation of swirl combustion.

Since current research on the oscillation mechanisms in swirl combustors predominantly focuses on swirl-stabilized premixed flames, this study focuses on a single-stage swirling diffusion flame and conducts experimental research to explore the mechanisms of thermoacoustic coupled oscillatory combustion. The flame's dynamic response to velocity fluctuations is examined, and a novel phase analysis model is established. The closed-loop feedback relationship between velocity fluctuations, pressure fluctuations, and fluctuations in the heat release rate is verified by this model. Compared to existing studies, this research innovatively analyzes the impact of the swirl number on oscillatory combustion, while the influence patterns and mechanisms of the equivalence ratio, inlet Reynolds number, and combustion chamber length on oscillatory combustion are revealed systematically. The findings indicate that decreases in the equivalence ratio, along with the increases in the inlet Reynolds number and swirl number, reduce the phase delay in heat release rate fluctuations—key factors contributing to increases in both the dominant oscillation frequency and oscillation intensity. Furthermore, an increase in the combustion chamber length reduces the system's resonance frequency, enhancing the acoustic feedback strength associated with the oscillation main frequency and thus intensifying the oscillations. Overall, the phase delay in heat release rate fluctuations in response to incoming velocity disturbances and the acoustic characteristics of the combustion system are crucial in affecting thermoacoustic coupling. The study provides a comprehensive interpretative approach to the mechanisms behind swirl oscillatory combustion.