ターボラムエンジン主燃焼器模型の水素燃焼試験結果

概要

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To obtain design data of a subsonic ram.combustor for a hypersonic plane, hydrogen combustion tests were were made by an approximately one-tenth scale model. It was composed of a constant area combustion duct, a flame holder and a center body which simulate the turbofan engine to be used as a booster for the take-off mode. The conditions of supplied air velocity, air temperature and mixture strength were equivalent to those of the combustor inlet at flight speeds ranging from take.off to Mach 3. Gas velocity and temperature distributions along the axis and the values of total pressure loss were obtained by measurements of total and static pressures. Combustion efficiency was derived from gas analysis of the sampled gas at the exit. It was found that the fuel distribution in the combustor makes significant effects on the combustion efficiency near stoichiometric mixture condition.
一般社団法人日本機械学会の論文
1990-01-25