液水/液酸7トン管構造燃焼器の試作と燃焼実験

概要

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A regeneratively cooled thrust chamber for 7-ton thrust rocket engine using LH_2-LOX as propellant has been fabricated and its performance has been demonstrated. This thrust chamber, with a reduced area ratio of 7 for sea-level running in comparison with 40 under vacuum condition, has 90-element coaxial injector distributed on a face plate made by pressed meshes for hydrogen transpiration cooling and it is equipped with a GH_2/GO_2 augmented spark igniter. The cooling jacket has been made by furnace brazing process, consisting of 199-tapered tubes, each with 0.3 mm thick SUS347,which is reinforced by a contoured SUS347 outer shell. The sea-level test facility has pressurized LOX and LH_2 tanks which provide a maximum burning duration of approximately 20 sec. Following the initial testing period during which the starting sequece and operating conditions have been established, the static-firing tests were conducted at a chamber pressure of about 25 kgf/cm^2 a and an oxidant-fuel ratio of about 5.0. The test results are discussed as compare wit the design conditions.
宇宙航空研究開発機構の論文