화염편 모델을 이용한 하이브리드 로켓의 연소과정 해석

다국어 초록 (Multilingual Abstract)

Hybrid propulsion systems provide many advantages in terms of stable operation and safety. However, classical hybrid rocket motors have lower fuel regression rate and combustion efficiency compared to solid propellant rocket motor. Accordingly, the recent research efforts are focused on the improvement of engine efficiency and regression rate in the hybrid rocket engine. The present study has numerically investigated the combustion processes in the hybrid rocket engine. The turbulent combustion is represented by the flamelet model and Low Reynolds number k-ε turbulent model is employed to reduce the uncertainties for convective heat transfer near solid fuel surface having strong blowing effect. Based on numerical results, the detailed discussions have been made for the effects of oxygen injection methods and oxygen injection flow rate on flame structure and regression rate in the vortex hybrid rocket engines.

목차 (Table of Contents)

• Abstract
• 1. 서론
• 2. 수치 모델
• 3. 연소 모델
• 4. 결과 및 해석
• 5. 결론
• 참고문헌