Numerical simulation on vortex shedding and combustion oscillation in aero-engine afterburner

The flow field and combustion oscillation in the aero-engine afterburner were numerically simulated.The mean parameter and vortex structure were obtained.The combustion model is very important for the shear vortex accreting the flame holder lip.The periodic process of vortex shedding and periodic change of recirculation zone after the flame holders were observed as an important factor for the afterburner buzz and combustion oscillation.The applicability of Rayleigh rule was validated by the harmonious wave in the afterburner.