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박정,김용욱,김영한,정용갑,조남경,오승협,Park, Jeong,Kim, Yong-Wook,Kim, Young-Han,Chung, Yong-Gahp,Cho, Nam-Kyung,Oh, Seung-Hyub 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.5
A model for depicting the rocket engine combustion process is presented and several experiments near a design point are provided with a FOOF type of unlike impinging injector for a propellant combination of Jet A-1 fuel and liquid-oxygen. The model is based on the assumption that the vaporization is the rate-controlling combustion process. The effects of initial drop size and initial drop velocity are systematically shown and discussed. It is seen that in the midst of considered parameters the change of initial drop size is more sensitive to the performance. The proposed model describes qualitative trends of combustion process well despite of its simplicity.
SINDA/FLUINT를 활용한 발사체 추진기관 공급계 해석
조남경(Nam-Kyung Cho),정용갑(Yong-Gahp Jeong),한상엽(Sang-Yeop Han),김영목(Young-Mog Kim) 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
The analysis of propellant feeding sub-system is performed using a commercial code SINDA/FLUINT, the comprehensive finite-difference, one-dimensional, lumped parameter tool. With the code, cryogenic helium supply system, liquid oxygen supply system, helium injection cooling system are evaluated. The code gave satisfactory estimation scheme for propulsion system characterized by cryogenic temperature and high pressure, two phase flow. This paper focuses on presenting calculation scheme of propulsion sub-system using one-dimensional code like SINDA/FLUINT.
액체 로켓 엔진에 있어서 추진제 공급 선점 시간에 따른 점화 특성에 관한 연구
박정,김용욱,김영한,이재룡,정용갑,조남경,오승협,Park, Jeong,Kim, Yong-Wook,Kim, Young-Han,Lee, Jae-Yong,Chung, Yong-Gahp,Cho, Nam-Kyung,Oh, Seung-Hyub 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.11
Experimental studies on determination of the supply leading time of propellants to combustion chamber have been made to stably and efficiently guarantee the ignitions process with liquid rocket engine. The propellant used is a Kerosene as fuel and a liquid oxygen as oxidizer. FOOF type of three injectors are set with an angle of 135。 and the combustion chamber pressure is 200psi. The present experiment program also includes the stability on the quadlet type of ignitor using the triehylaluminum (TEAL) as an ignition source. Experimental results clarifies that the propellant supply through LOx leading to combustion chamber is proper for stable ignition and combustion processes based on the fuel and oxidizer manifold pressures, combustion chamber pressure, and the variation of flame length from the nozzle exit with lapse time, and shows that the leading supply time pf propellants effects the engine performance little.