Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Combustion Characteristics Based on Injector Shape of Supersonic Combustor

초음속 연소기의 인젝터 형상에 따른 연소특성

  • Jin, Sangwook (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Choi, Hojin (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Lee, Hyung Ju (Division of Aeronautics, Cheongju University) ;
  • Byun, Jong-Ryul (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Bae, Juhyun (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Park, Dongchang (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
  • Received : 2018.06.03
  • Accepted : 2019.05.01
  • Published : 2019.06.01
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Abstract

A direct connected test was conducted for a supersonic combustor with a cavity-type flame holder. Liquid hydro-carbon fuel was injected in different types of injectors: inclined and aeroramp injectors, for the flow condition of Mach 4 at an altitude of 20 km. The static pressure on the combustor wall along the axis and the total pressure at the exit of combustor were measured to analyze the combustion characteristics at various fuel flow rates.

공동형 화염 안정화 장치를 갖는 초음속 연소기를 직접 연결 방식으로 시험을 수행하였다. 고도 20 km, 비행 마하수 4에 해당하는 전온도, 전압력 유동 조건에 대해 액체 탄화 수소 연료를 경사 분사와 공력 램프 분사의 2가지 방법으로 분사하였다. 축방향 벽면 압력과 연소기 출구의 전압력을 계측하여 연료량에 따른 연소 특성을 파악하였다.

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References

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