Abstract
The purpose of this study is to conduct a comprehensive study on the flow characteristics in a combustor with seven swirl injectors. The analysis is based on a 3D large eddy simulation (LES) technique. The propellant properties are defined by a surrogated model of Jet-A fuel and air mixture. Two combustors of counter-swirl injectors (four-clockwise and three-counterclockwise-swirl injectors) and co-swirl injectors (seven-clockwise-swirl injectors) are simulated to identify the effect of swirl direction. The detail turbulent flow structures; a corner recirculation zone (CRZ) and a central toroidal recirculation zone (CTRZ), are observed and the flow interactions among swirl injectors in each combustor are visualized. Pressure oscillation in the combustor was numerically investigated and compared with theoretical results based on linear theory to determine the dominant acoustic modes.
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