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飛行マッハ数8-15における縦渦導入型スクラムジェット燃焼器の性能
https://jaxa.repo.nii.ac.jp/records/17249
https://jaxa.repo.nii.ac.jp/records/17249a97d98ae-0583-4761-bc05-f4f34395d012
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 飛行マッハ数8-15における縦渦導入型スクラムジェット燃焼器の性能 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スクラムジェットエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高速 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝撃波 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙輸送 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エンタルピー | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | モデル | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | scramjet engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high speed | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combustion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock wave | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | space transportation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | enthalpy | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | model | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Effects of streamwise vortices on scramjet combustion at Mach 8-15 flight enthalpies | |||||
著者 |
須浪, 徹治
× 須浪, 徹治× 伊藤, 勝宏× 女屋, 聡史× 高橋, 政浩× 小室, 智幸× 佐藤, 和雄× Sunami, Tetsuji× Ito, Katsuhiro× Onaya, Satoshi× Takahashi, Masahiro× Komuro, Tomoyuki× Sato, Kazuo |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
東北大学 大学院 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) | |||||
書誌情報 |
宇宙輸送シンポジウム 平成15年度 en : Proceedings of Space Transportation Symposium FY2003 p. 73-76, 発行日 2004-04 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The effect of streamwise vortices on the scramjet combustion performance under flight Mach 8 to 15 was investigated. Combustion experiments of a hydrogen fueled scramjet engine model were conducted at the HIEST (High Enthalpy Shock Tunnel) of JAXA at a combustor entrance Mach number of 5 and a total equivalence ratio of 0.5. Two kinds of fuel injectors, which generated streamwise vortices of different circulation to enhance fuel/air mixing and combustion, were examined. For comparison, another two injectors called back step ramp injector and back step injector were also tested. The former injector generates strong shock wave and the latter generates no strong disturbances. Pressure measurements in the combustor showed 1) that, in all the conditions tested, streamwise vortices of large circulation achieved the highest pressure rise due to combustion, 2) that, in the case of the fuel injectors generating streamwise vortices, the apparent peak of pressure rise is observed at the total enthalpy of 7 to 8 MJ/kg, 3) that back step ramp injector generating strong shock wave obtained poor combustion at the total enthalpy of 5 to 10 MJ/kg except good combustion at 4 MJ/kg, and 4) that back step injector without strong disturbance obtained poor combustion at the total enthalpy of 4 to 7 MJ/kg except good combustion at 10 MJ/kg. Results showed that the use of strong streamwise vortices is quite effective to obtain good scramjet combustion performance through the high flight Mach numbers, 8 to 15. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0047118019 |