Experimental investigation of soot concentration distribution in an aero-engine combustor using two-color laser-induced incandescence

The spatiotempor important for assessing its c of soot concentration in term al distribution of soot concentration in aero-engine combustor is ombustion performance. Here, we report experimental measurements s of Soot Volume Fraction (SVF) and its spatiotemporal distribution a single-sector dual-swirl aero-engine combustor using Two-Color Laser-Induced Incandescence (2C-LII). It is shown that soo bustion zone, exhibiting a V-type distribution with higher concentration in the lower half of the zone than the upper half, wit emissions at the combustor o t predominantly forms in the symmetrical vortices of the primary comh a small amount distributed in the secondary recirculation zone. Soot utlet are relatively low under three typical operating conditions by LII experiments, which is aligned temperature on SVF distribu suggests that the SVF level in perature. Meanwhile, the SVF distribution becomes more symmetrical as the inlet temperature increases, although the overall SVF level in the lower half of the zone is still higher. We also investigate the influence of the inl with Smoke Number (SN) from gas analysis. The effect of inlet air tion and dynamics in the primary combustion zone is studied, which the primary combustion zone monotonically increases with the temet air pressure on the SVF distribution at the combustor outlet. The soot concentration at the combu larly across both sides and th exhibits dot-like and linear patt flow field in the primary combu behavior. These results unde performance of this specific future. e ce stor outlet increases with inlet pressure, mainly distributed irregunter. On both sides, the distribution is continuous, while the center erns. Numerical simulations correlated SVF distribution with the stion zone, qualitatively explaining the observed SVF distribution r various conditions can provide valuable insights for improving the combustor and designing high-temperature-rise combustors in the (c) 2025 The Authors. Publ ished by Elsevier Ltd on behalf of Chinese Society of Aeronautics and Astronautics. This is an open acces s article under the CC BY-NC-ND license (http://creativecommons.org/ licenses/by-nc-nd/4.0/).