한국연소학회:학술대회논문집

한국연소학회 (The Korean Society of Combustion)
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액체로켓엔진 가스발생기 연소특성

Combustion Characteristics of Gas Generator for Liquid Rocket Engine

  • 김승한 (한국항공우주연구원 엔진그룹) ;
  • 한영민 (한국항공우주연구원 엔진그룹) ;
  • 문일윤 (한국항공우주연구원 엔진그룹) ;
  • 이광진 (한국항공우주연구원 엔진그룹) ;
  • 설우석 (한국항공우주연구원 엔진그룹) ;
  • 이창진 (건국대학교 항공우주공학과) ;
  • 김승한 (한국항공우주연구원 엔진그룹)
  • 발행 : 2004.11.26
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초록

The results of combustion performance test of fuel-rich gas generator(GG) using LOx and kerosene as propellant at design and off-design point are described. The parameters used in this analysis are the average exit temperature($T_{GG}$) and the characteristic velocity($C^{\ast}$). The average gas temperature at the exit of gas generator is found to be a function of propellant O/F ratio. For the gas generator having residence time of 4msec or more, the effect of flame residence time and combustion chamber pressure on the exit temperature is not significant. The exit characteristic velocity is found to be linearly proportional to the gas temperature at the exit of gas generator.

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