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液水/液酸7トン管構造燃焼器の試作と燃焼実験
https://jaxa.repo.nii.ac.jp/records/32827
https://jaxa.repo.nii.ac.jp/records/32827bdff1693-3972-43e4-892b-ff67e71b1838
名前 / ファイル | ライセンス | アクション |
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SA0166596.pdf (2.7 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 液水/液酸7トン管構造燃焼器の試作と燃焼実験 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Development of Tubular Wall Thrust Chamber for LH_2/LOX Rocket engines | |||||
著者 |
倉谷, 健治
× 倉谷, 健治× 秋葉, 鐐二郎× 長友, 信人× 岩間, 彬× 橋本, 保成× 棚次, 亘弘× 加勇田, 清勇× 成尾, 芳博× 小林, 清和× 林, 哲史× 外川, 守人× 加藤, 文雄× Kuratani, Kenji× Akiba, Ryojiro× Nagatomo, N.× Iwama, Akira× Hashimoto, Yasunari× Tanatugu, Nobuhiro× Kayuta, Seiyu× Naruo, Yoshihiro× Kobayaski, Koyokazu× Hayashi, T.× Togawa, M.× Kato, Fumio |
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著者所属 | ||||||
三菱重工業KK | ||||||
著者所属 | ||||||
三菱重工業KK | ||||||
著者所属 | ||||||
川崎重工業KK | ||||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science | |||||
書誌情報 |
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 巻 6, p. 167-192, 発行日 1983-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 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. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0285-9920 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00354485 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0166596000 |