Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Regenerative Cooling Channel Design of a Supersonic Combustor Considering High-Temperature Property of Fuel

연료 고온물성을 고려한 초음속 연소기 재생냉각 유로 설계

  • Yang, Inyoung (Engine System Research Team, Korea Aerospace Research Institute)
  • Received : 2018.02.09
  • Accepted : 2018.07.19
  • Published : 2018.12.01
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Abstract

A design study on the cooling channel configuration in a regeneratively cooled supersonic combustor was performed. The flow parameters on the hot- and cold-side channels were calculated using a quasi-one-dimensional model. The heat transfer between these two sides was estimated as a part of the flow calculation. For the reference configuration, the total amount of heat exchanged was 10.7 kW, the heat flux was $566kW/m^2$, and the fuel temperature increase between the inlet and outlet was 153 K. Seven designs of the heat exchanger channel were compared for their heat transfer performance.

초음속 연소기에 대해 연료에 의한 연소기 재생 냉각을 가정하여 재생 냉각 유로 형상 설계를 수행하였다. 준일차원 모델을 사용하여 고온 측 및 저온 측 유동 계산을 수행하였으며 이 과정에서 양쪽 사이의 열전달을 계산하였다. 기준 형상에서 총 열교환량은 10.7 kW, 열유속은 $566kW/m^2$, 열교환기 입출구에서의 연료 온도 변화는 153 K으로 계산되었다. 7개의 열교환기 유로 형상에 대하여 열전달 성능을 비교하였다.

Keywords

References

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