한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제21권1호
  • /
  • Pages.36-43
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  • 2017
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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Canted Slit 형상의 핀틀 인젝터 로켓엔진의 특성길이와 운동량비에 따른 연소성능

Combustion Performance of a Pintle Injector Rocket Engine with Canted Slit Shape by Characteristic Length and Total Momentum Ratio

  • Yu, Isang (School of Aerospace Engineering, Chungnam National University) ;
  • Kim, Sunhoon (School of Aerospace Engineering, Chungnam National University) ;
  • Ko, Youngsung (School of Aerospace Engineering, Chungnam National University) ;
  • Kim, Sunjin (Fire Safety Engineering, Korea Chungnam State University) ;
  • Lee, Janghwan (Launcher Propulsion System Team, Korea Aerospace Research Institute) ;
  • Kim, Hyungmo (Engine Parts Research Team, Korea Aerospace Research Institute)
  • 투고 : 2016.10.28
  • 심사 : 2016.12.05
  • 발행 : 2017.02.01
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초록

본 연구에서는 케로신과 액체산소를 추진제로 사용하는 핀틀 인젝터의 설계/제작이 이루어졌으며, 연소실 특성길이와 운동량비에 따른 특성속도효율을 통해 연소성능을 확인하였다. 연소시험 결과, 핀틀 인젝터의 추진제 분무 특성으로 인한 재순환영역에 의해, 추진제 조합에 따른 특성길이 추천치보다 짧은 영역에서도 최적의 연소성능을 발휘하는 것을 확인하였다. 또한 운동량비가 연소성능에 지대한 영향을 미치나, 추천범위 1.0~1.5 내에서 특성속도효율이 일정하게 나타남을 확인하였다.

In this study, a pintle injector rocket engine which uses kerosene and liquid oxygen as propellants was manufactured by collecting basic design data and establishing a design procedure. Combustion performance of the liquid rocket engine was investigated by characteristic velocity efficiency with characteristic length of the combustion chamber and total momentum ratio. As a result of hot fire tests, it showed that the engine had shorter characteristic length comparing to those of other type injectors, which was known as recommended value with the propellant combination. Also, the characteristic velocity efficiency was greatly affected by total momentum ratio and almost constant within 1.0~1.5.

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참고문헌

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