Proceedings of the KSME Conference (대한기계학회:학술대회논문집)

The Korean Society of Mechanical Engineers (대한기계학회)
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The Combustion Characteristics of a Subscale Engine of KSRIII(I)

KSR-III 엔진 축소형 모델 연소 특성(I)

  • 김영한 (한국항공우주연구원 추진기관연구부) ;
  • 김용욱 (한국항공우주연구원 추진기관연구부) ;
  • 고영성 (한국항공우주연구원 추진기관연구부) ;
  • 이수용 (한국항공우주연구원 추진기관연구부) ;
  • 류철성 (한국항공우주연구원 추진기관연구부) ;
  • 설우석 (한국항공우주연구원 추진기관연구부)
  • Published : 2001.06.27
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Abstract

For the successful development of the main engine of KSR(Korea Sounding Rocket)-III, Korea Aerospace Research Institute(KARI) carried out the experimental study on the subscale model engines. Several types of engines were tested on the Small Liquid Rocket Engine Test Facility. One of the typical test results of a Sub. engine(Sub. Mod.3) is presented here. It uses the Jet A-1 as fuel, liquid oxygen as oxidizer, and Tri-Ethyl Aluminium(TEA1) as ignition agent. The gas pressure feed system is adopted as a feeding mechanism and the design chamber pressure is 200psia. The physical phenomena are described in three regimes(ignition, transient, and steady state) with the pressure, thrust, flowrate and image data. And the pressure oscillation is analyzed in Fourier domain (<500Hz). Then we conclude that in this experiment, the engine shows the characteristic low frequency of 80Hz and it is stable for that frequency of pressure oscillation.

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