Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Ramjet Mode Combustion Test for a Dual-Mode Ramjet Engine Model with a Large Backward-Facing Step

큰 후향 계단이 있는 이중 모드 램젯 엔진 모델의 램젯 모드 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) ;
  • Kim, Chun-taek (Engine System Research Team, Korea Aerospace Research Institute)
  • Received : 2016.06.07
  • Accepted : 2016.10.26
  • Published : 2016.12.01
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Abstract

Ramjet mode combustion test was performed for a dual-mode ramjet engine model. The engine model consists of an air intake, a combustor and a nozzle. The combustor in the model has a large backward-facing step, designed to be used as a part of a rocket-based combined cycle engine. The test was performed at the flight speed of Mach 5 and the altitude of 24 km. Strong combustion was established only when the fuel was injected from both of the bottom-side and cowl-side wall. When the total fuel stoichiometric ratio was 1.0, distributed as 0.5 on the cowl side and 0.5 on the bottom side, the flow became subsonic at some portion in the combustor by thermal choking, i.e., ramjet mode was established for this condition.

이중 모드 램젯 엔진 모델의 램젯 모드 연소 시험을 수행하였다. 엔진 모델은 흡입구, 연소기 및 노즐로 이루어졌다. 로켓 기반 복합 사이클 엔진에 사용하는 것을 전제로 큰 후향 계단을 가지는 형상을 선택하였다. 시험은 마하 5, 고도 24 km 조건에서 수행하였다. 연료를 카울면과 바닥면에 분산하여 다중 분사를 한 경우에 안정적인 연소를 달성할 수 있었다. 또한 연료 당량비를 카울면에서 0.5, 바닥면에서 0.5로 하여 총 당량비 1.0으로 한 경우에 연소기 내부에서 열질식이 발생하여 유동이 아음속으로 조성되는 램젯 모드로 운전됨을 확인하였다.

Keywords

References

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Cited by

  1. Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility vol.22, pp.3, 2018, https://doi.org/10.6108/KSPE.2018.22.3.001