Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
巻
JAXA-SP-05-010
ページ
81 - 86
発行年
2006-01-20
抄録（英）
To improve scramjet combustor performance at the hypervelocity condition corresponding to flight Mach number from 10 to 15, optimization possibility of the combustion gas temperature was investigated based on combustion experiment of a large-scale scramjet engine using a large free-piston driven shock tunnel. A previous engine model was designed so that the gas temperature at the combustor entrance would become around 1,200 K at the hypervelocity condition to prevent excessive loss in the net heat release due to thermal dissociation of the combustion gas. The results showed that the pressure rise due to combustion was large at the beginning of the test time but dropped drastically as time progressed. It was considered that the heat release obtained in the combustor was not sufficient to maintain intensive combustion. Following the discussion above, a new scramjet engine model (M12-02) was designed with an aim of promoting combustion heat release and establishing steady intensive combustion. The inlet compression ratio of the M12-02 WZLS increased to raise the static temperature and density of the flow at the combustor entrance. As a result of the design modification, the pressure rise due to combustion increased and the duration of intensive combustion was extended. The combustor performance became the highest at stagnation enthalpy of 7 MJ/kg, which was the design condition of the M12-02, and it was considered that the remarkable improvement in the combustor performance was achieved by establishing both adequately low gas temperature in the combustor and fairly stable combustion. Application of a Hyper-Mixer (HM) injector to the M12-02 was attempted with an aim of further improvement in the combustion stability and the combustor performance. The combustion test results showed that the HM injector was quite effective in establishing steady intensive combustion at the hypervelocity condition. In addition to the improvement in the mixing rate, capability in ignition and flame-holding at very low gas temperature condition was improved and high combustor performance was obtained at the low enthalpy condition. However, the combustor performance with the HM injector dropped as the stagnation enthalpy increased and became almost the same as that with a simple back-step injector at the enthalpy condition of 7 MJ/kg or higher.
スクラムジェットエンジン高速化の研究
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