Transactions of the Korean Society of Mechanical Engineers B (대한기계학회논문집B)

The Korean Society of Mechanical Engineers (대한기계학회)
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A Study on Ignition Characteristic with Supply Leading Time of Propellants in Liquid Rocket Engine

액체 로켓 엔진에 있어서 추진제 공급 선점 시간에 따른 점화 특성에 관한 연구

  • 박정 (순천대학교 기계자동차공학부) ;
  • 김용욱 (한국항공우주연구소 우주추진연구그룹) ;
  • 김영한 (한국항공우주연구소 우주추진연구그룹) ;
  • 이재룡 (한국항공우주연구소 우주추진연구그룹) ;
  • 정용갑 (한국항공우주연구소 우주추진연구그룹) ;
  • 조남경 (한국항공우주연구소 우주추진연구그룹) ;
  • 오승협 (한국항공우주연구소 우주추진연구그룹)
  • Published : 2000.11.01
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Abstract

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.

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References

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