Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Numerical Study on the Process of Supersonic Flow Formation in a Direct-Connect Supersonic Combustor

Direct-Connect 초음속 연소기 내 초음속 유동 형성과정에 대한 수치해석

  • Jeong, Seong-Min (Department of Aerospace Engineering, Pusan National University) ;
  • Han, Hyunh-Seok (Department of Aerospace Engineering, Pusan National University) ;
  • Sung, Bu-Kyeng (Department of Aerospace Engineering, Pusan National University) ;
  • Lee, Eun-Sung (Department of Aerospace Engineering, Pusan National University) ;
  • Choi, Jeong-Yoel (Department of Aerospace Engineering, Pusan National University)
  • Received : 2020.09.10
  • Accepted : 2020.10.26
  • Published : 2020.11.01
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Abstract

In this study, a numerical analysis was performed to confirm the formation of supersonic flow and the stabilization time satisfying the design condition in a Direct-connect supersonic combustor. The process was examined in which the high-pressure gas of vitiation air heater propagates downstream to the supersonic combustor and forms a supersonic flow field. It was confirmed through the analysis of pressure and temperature that the supersonic flow field satisfies the design points of Mach number 2.0 and 1,000 K, and requires a minimum of 4.0 ms for stabilization. These results indicate that the time required for the supersonic flow field stabilization should be taken into account when testing for the supersonic combustion experiment.

본 연구에서는 직접 연결식 초음속 연소기에서 설계점을 만족하는 초음속 유동의 형성유무 및 안정화 소요시간을 확인하기 위한 수치해석이 수행되었다. 이를 위하여 연소식 공기 가열기 하류의 고압 유동이 초음속 연소기로 전파되며 초음속 유동장을 형성해가는 과정을 살펴보았다. 압력 및 온도 분석을 통해, 초음속 유동장이 설계점인 마하수 2.0, 1,000 K을 만족하며, 최소 4.0 ms의 안정화 시간이 필요함을 확인하였다. 따라서 초음속 연소시험에서 연료분사 이전에 유동 안정화에 필요한 시간을 고려해야 함을 알 수 있었다.

Keywords

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