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

The Korean Society of Mechanical Engineers (대한기계학회)
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Design and Experimental Verification of Uni-Injector Using Gas Methane and Lox as Propellants

가스메탄/액체산소를 추진제로 하는 단일 인젝터 설계 및 실험적 검증

  • Jeon, Jun Su (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Min, Ji Hong (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Jang, Ji Hun (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Ko, Young Sung (Dept. of Aerospace Engineering, Chungnam Nat'l Univ.) ;
  • Kim, Sun Jin (Fire Safety Engineering, Chungnam Provincial Cheongyang College)
  • 전준수 (충남대학교 항공우주공학과) ;
  • 민지홍 (충남대학교 항공우주공학과) ;
  • 장지훈 (충남대학교 항공우주공학과) ;
  • 고영성 (충남대학교 항공우주공학과) ;
  • 김선진 (충남도립 청양대학 소방안전관리)
  • Received : 2012.06.14
  • Accepted : 2012.12.28
  • Published : 2013.03.01
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Abstract

An injector that uses methane gas ($CH_4$) and liquid oxygen ($LO_x$) as propellants was designed to verify the combustion characteristics of an engine that uses methane, which is one of the next-generation propellants. A swirl/shear coaxial-type injector was used, and flow analysis was performed using Fluent to determine the main design parameters of the injector. A hydraulic test was performed to understand the atomization and spray pattern characteristics of the injector. Next, a combustion test was performed at the design point to understand the ignition and combustion stability. Additional combustion tests were performed according to the O/F ratio to investigate the combustion characteristics and stabilities using the characteristic exhaust velocity ($C^*$) and fluctuation of the chamber pressure. The experimental results showed that the combustion efficiency was greater than 90%, and the pressure fluctuation was lower than 2% under all conditions.

차세대 로켓 엔진의 추진제중 하나로 부각되어지고 있는 메탄 엔진의 연소 특성을 파악하기 위하여 가스메탄과 액체산소를 추진제로 사용하는 로켓 엔진의 인젝터를 설계/제작 하였다. 동축 스월/전단형 인젝터를 채택하여 제작하였으며, 상용 해석 프로그램인 Fluent를 사용하여 유동해석을 수행한 결과를 바탕으로 인젝터의 주요 변수들을 선정하였다. 제작된 인젝터는 수류실험을 통하여 미립화와 분무특성을 파악하였고, 설계점에서의 연소실험을 수행하여 점화 및 연소 안정성을 확인하였다. 또한, 혼합비(O/F ratio)를 변화시켜가며 연소 실험을 수행하여 특성 속도($C^*$)와 연소실 압력 섭동 값을 이용하여 연소 특성 및 안정성을 평가하였다. 실험 결과 모든 혼합비 영역에서 평균적으로 90% 이상의 높은 연소 효율을 보였고, 압력 섭동 값이 2% 미만으로 연소안정성을 확인하였다.

Keywords

References

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