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Performance Sensitivity Analysis of Liquid Rocket Engine  

Cho, Won Kook (엔진팀)
Park, Soon Young (엔진팀)
Publication Information
Aerospace Engineering and Technology / v.12, no.1, 2013 , pp. 200-206 More about this Journal
Abstract
A performance sensitivity of liquid rocket engine to propellant density or supply pressure change was studied. The analysis program was verified to have 1% error comparing with the measured data of a turbopump-gas generator system. The engine combustion pressure decreases as fuel supply pressure increases due to decreased mixture ratio which reduces the turbine power. The engine combustion pressure increases as fuel density increases because the total propellant flow rate is increased substantially even though mixture ratio is slightly decreased. The engine combustion pressure increases when the oxidizer density or supply pressure increases.
Keywords
systems analysis; gas generator cycle; liquid rocket engine; sensitivity analysis;
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  • Reference
1 남창호, 김승한, 설우석, 2007, "성능 분산을 고려한 액체로켓엔진의 시스템 시험 영역 설 정," 한국추진공학회 2007년도 추계학술대회 논문집, pp. 165-169.
2 Dixon, S.L. and Eng, B., 1998, Fluid mechanics, thermodynamics of turbomachinery 3rd Ed., Butterworth- Heinemann, p.8
3 조원국, 박순영, 남창호, 김철웅, 2010, "추진제 공급압력이 액체로켓엔진의 성능에 미치는 영향," 대한기계학회논문집 B권, 제34권, 제4호, pp.433-448.
4 박순영, 조원국, 2008, "가스발생기 사이클 액 체로켓 엔진의 모드 해석 프로그램 개발," 한국추진공학회 2008년도 추계학술대회 논문집, pp. 366-370.
5 McBride, B. J. and Gordon, S., 1996, Computer program for calculation of complex chemical equilibrium compositions and applications, NASA Reference Publication 1311.
6 서성현, 한영민, 김성구, 최환석, 2006, "연료 과농 가스발생기의 연소 가스 물성치에 관한 연구," 한국추진공학회 2006년도 춘계학술대회 논문집, pp.118-122.
7 김철웅, 박순영, 남창호, 2009, 터보펌프-가스 발생기-연소기 시스템의 모드해석, 한국항공우주연구원, KARI-RET-TM-2009-009