Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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A Numerical Study on Cooling Characteristics of a Rocket-engine-based Incinerator Devised for High Burning Rate of Solid Particles

고체입자의 높은 연소율을 갖기 위해 고안된 로켓 엔진 기반 소각로의 냉각 해석

  • Son, Jinwoo (School of Mechanical and Aerospace Engineering, Sejong University) ;
  • Sohn, Chae Hoon (School of Mechanical and Aerospace Engineering, Sejong University)
  • Received : 2016.01.01
  • Accepted : 2016.03.07
  • Published : 2016.04.01
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Abstract

Cooling characteristics are investigated numerically in the chamber for high-performance burnout of wastes with solid phase. Before the combustion chamber is manufactured, combustion analysis is performed for evaluation of burning rate and cooling performance. A water cooling method is applied and its feasibility for cooling is examined depending on coolant flow rate. Another method of complex cooling is adopted by combining air film cooling with water cooling, leading to improved cooling performance.

고성능 고체 입자 연소를 위해 제안된, 로켓 엔진 기술이 접목된 연소실이 기존 연구를 통해 제시되었고, 본 연구에서는 연소실 벽면의 냉각해석을 수행하였다. 실제 연소실 제작에 앞서 연소율과 함께 냉각성능을 평가하기 위한 수치해석을 수행하였다. 연소실 벽면을 냉각하는 방식중 수냉각 방법을 적용하였고, 연소해석을 수행하여 선정한 냉각유량의 적정성을 검증하였다. 그리고 수냉각과 병행하여 공기 막냉각 방법을 이용한 복합냉각 방식을 적용한 수치해석 연구를 수행하였다. 해석 결과, 공기 막냉각만을 적용한 방식보다 막냉각과 수냉각을 복합적으로 적용한 냉각 방식이 더 우수한 냉각성능을 보였으며, 적용 가능한 범위의 냉각 유량을 산출하였다.

Keywords

References

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