The Characteristic Study on Mixture Ratio Stabilizer for Gas Generator of LRE(Liquid Rocket Engine)

액체로켓엔진 가스발생기 혼합비 안정기의 특성 연구

  • 정태규 (한국항공우주연구원 추진제어그룹) ;
  • 이중엽 (한국항공우주연구원 추진제어그룹) ;
  • 한상엽 (한국항공우주연구원 추진제어그룹) ;
  • 권세진 (한국과학기술원 항공우주공학)
  • Published : 2006.08.23

Abstract

The propellant mixture ratio of gas generator changes when thrust control valve operate to change LRE thrust level. The mixture ratio change of gas generator result in gas temperature change and failure of turbine blade or deterioration of LRE specific impulse. The mixture ratio stabilizer has been developed to maintain propellant mixture ratio of gas generator. This article deals with design and static/dynamic characteristic of stabilizer. Also gas generator system simulation test has shown that the stabilizer can maintain propellant mixture ratio effectively within tolerable range.

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