Proceedings of the KSME Conference (대한기계학회:학술대회논문집)

The Korean Society of Mechanical Engineers (대한기계학회)
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Effect of Combustion Chamber Pressure to Specific Impulse of Liquid Rocket Engine

액체로켓엔진에서 연소압이 비추력에 미치는 영향

  • 조원국 (한국항공우주연구원 엔진팀) ;
  • 박순영 (한국항공우주연구원 엔진팀) ;
  • 설우석 (한국항공우주연구원 엔진팀)
  • Published : 2008.11.05
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Abstract

A liquid rocket engine performance has been analyzed as a function of combustion pressure with LOx/RP-1R. The present method is verified by comparing the specific impulse for various combustion pressure with given pump head model. The optimal combustion pressure is between 150 bar and 200 bar for given efficiencies. Both the optimal combustion pressure and the specific impulse increase for increased turbine efficiency. The optimal combustion pressure decreases and the specific impulse increases for increased combustion efficiency. The pump efficiency and the turbine inlet temperature have the same qualitative effect as the turbine efficiency.

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