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

The Korean Society of Mechanical Engineers (대한기계학회)
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Study on Cooling Characteristics of Mixed Gases with Hot Gas of Liquid Rocket Engine and Injected Liquid Nitrogen

액체로켓엔진의 연소가스와 액체질소 혼합에 의한 연소 가스 냉각 특성에 관한 연구

  • Jeon, Jun-Su (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Yu, I-Sang (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Kim, Joong-Il (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Kim, Jai-Ho (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Ko, Young-Sung (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.)
  • 전준수 (충남대학교 항공우주공학과) ;
  • 유이상 (충남대학교 항공우주공학과) ;
  • 김중일 (충남대학교 항공우주공학과) ;
  • 김재호 (충남대학교 항공우주공학과) ;
  • 고영성 (충남대학교 항공우주공학과)
  • Received : 2012.05.24
  • Accepted : 2012.08.08
  • Published : 2012.10.01
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Abstract

In this study, the cooling characteristics of combustion gas were investigated by injecting liquid nitrogen ($LN_2$) into a liquid rocket combustion chamber, which uses liquid oxygen (Lox) and kerosene as propellants. $LN_2$ injectors and an extended chamber for mixing were installed at the end of the ordinary LRE combustion chamber, and a nozzle was installed after the chamber for mixing. First, an ignition test of the liquid rocket engine was conducted to verify the stable combustion process. Next, a hot firing test was performed step-by-step for safety. Finally, the test was performed for 20 s. The results showed that the combustion gas of the LRE could be successfully cooled by using $LN_2$.

본 연구에서는 액체산소와 케로신을 추진제로 사용하는 액체로켓엔진의 연소 가스에 액체질소를 분사하여 연소 가스의 냉각 특성을 알아보고자 하였다. 일반적인 액체로켓엔진의 연소실 후단에 액체질소 분사기와 혼합용 연소실을 추가적으로 장착하였고, 혼합용 연소실 후단에 노즐을 연결하여 전체적인 시스템을 구성하였다. 연소실험은 안전을 고려하여 점화실험부터 순차적으로 수행하였으며, 최종적으로 20초 연소실험을 수행하였다. 그 결과 기존의 액체로켓엔진에 액체질소를 분사함으로써, 연소 가스의 온도를 저하시킬 수 있음을 확인하였다.

Keywords

References

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