水素燃料噴流保炎型ラム燃焼器の高温燃焼特性

概要

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An innovative ramjet combustor with a jet mixing flame holding is now under investigation to apply to a space plane propulsive system. This jet mixing type ram combustor has some advantages, such as no obstruction in the main flow field, easy cooling for heated components and aerodynamically nonsensitivity to the flow distribution upstream. Following to the previous experimental investigation at 600K, which corresponds to the air temperature at Mach 3 in the flight speed, a series of combustion tests was conducted here at temperature level between 600K and 1200K, corresponding to Mach 3〜5 conditions. The length of the combustion duct was canged and the effect on the combustion efficiency was discussed. The pressure loss factor was remained within the value demanded from the engine system evaluation.
社団法人日本ガスタービン学会の論文
1995-09-10