단계식 연소사이클 로켓엔진용 삼중분사 예연소기의 초임계 화염구조 해석

Abstract

This study has been mainly motivated to numerically model the triplex injector preburner combustion which is operated in supercritical conditions encountered in rocket engine cycle. In the present approach, turbulence is represented by the standard k-e model. To account for the real fluid effects, the propellant mixture properties are calculated by using generalized cubic equation of state. In order to realistically represent the turbulence-chemistry interaction in the turbulent nonpremixed swirl flames, the flamelet approach based on the real fluid flamelet library has been adopted. Based on numerical results for triplex injector preburner, the detailed discussions are made for the effects of O/F ratio, pressure on Kerosene/LOx flame structure in supercritical conditions..