액체로켓 엔진 연소기에 장착되는 동축 스월 분사기의 액막 분열 및 분무 특성에 대한 수치적 연구

This study investigated the characteristics of spray generated by a liquid-liquid co-axial swirl injector used in a combustor of the liquid rocket engine. The linear stability analysis[1] was introduced in liquid sheet breakup and Post[2]'s collision model which considers shattering was adopted on the collision model after breakup. Every model was implemented to KIVA[3], which was adopted as a solver. To validate the implemented models the case of low injection velocity which was similar to a injector installed in LRE main combustor was calculated and the result agreed well with test result.