Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility

직결형 설비를 이용한 초음속 연소기 연소 시험

  • Yang, Inyoung (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Lee, Kyung-Jae (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Lee, Yang-Ji (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Lee, Sanghoon (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Kim, Hyungmo (Engine Component Research Team, Korea Aerospace Research Institute) ;
  • Park, Poomin (Engine Component Research Team, Korea Aerospace Research Institute)
  • Received : 2017.09.18
  • Accepted : 2017.12.24
  • Published : 2018.06.01
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Abstract

A combustion test for a supersonic combustor was conducted using a direct-connected type supersonic combustor test facility. The facility was verified for the capability of simulating required flow conditions. The test condition was maintained at Mach 2.0, $915^{\circ}C$ and 496 kPa for 15 s. Using gaseous hydrogen as the fuel, the combustor model was also tested for its ignition and flame holding capability at the fuel equivalence ratio of 0.12. Combustion efficiency was 71%, and the supersonic flow regime was obtained at this test condition.

직결형 초음속 연소기 시험 설비를 사용하여 초음속 연소기에 대한 연소 시험을 수행하였다. 설비는 필요한 유동 조건을 모사할 수 있음을 검증하였다. 시험 조건은 유속 마하 2.0, 온도 $915^{\circ}C$, 압력 496 kPa을 15초 동안 모사할 수 있었다. 연소기 모델은 기체 수소를 연료로 사용하여 연료 당량비 0.12에서 점화 및 화염 유지가 가능함을 검증하였다. 이 유동 조건에서 연소 효율은 71%였으며 초음속 유동이 유지되었다.

Keywords

References

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