@article{oai:jaxa.repo.nii.ac.jp:00032827,
 author = {倉谷, 健治 and 秋葉, 鐐二郎 and 長友, 信人 and 岩間, 彬 and 橋本, 保成 and 棚次, 亘弘 and 加勇田, 清勇 and 成尾, 芳博 and 小林, 清和 and 林, 哲史 and 外川, 守人 and 加藤, 文雄 and Kuratani, Kenji and Akiba, Ryojiro and Nagatomo, N. and Iwama, Akira and Hashimoto, Yasunari and Tanatugu, Nobuhiro and Kayuta, Seiyu and Naruo, Yoshihiro and Kobayaski, Koyokazu and Hayashi, T. and Togawa, M. and Kato, Fumio},
 journal = {宇宙科学研究所報告. 特集: 液水/液酸エンジンの開発研究報告},
 month = {Mar},
 note = {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., 資料番号: SA0166596000},
 pages = {167--192},
 title = {液水/液酸7トン管構造燃焼器の試作と燃焼実験},
 volume = {6},
 year = {1983}
}