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液体ロケットエンジン用低反動度超音速タービンにおける効率低下の数値予測技術について
https://jaxa.repo.nii.ac.jp/records/16583
https://jaxa.repo.nii.ac.jp/records/16583dc7b5c2d-8e14-461f-9519-ff3d517fd218
Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 液体ロケットエンジン用低反動度超音速タービンにおける効率低下の数値予測技術について | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Rocket Engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Supersonic Turbine | |||||
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 | Numerical Prediction of Performance Decrease for a Supersonic Reaction Turbine of a Liquid Rocket Engine | |||||
著者 |
河津, 要
× 河津, 要× 谷, 直樹× 山西, 伸宏× Kawatsu, Kaname× Tani, Naoki× Yamanishi, Nobuhiro |
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著者所属 | ||||||
宇宙航空研究開発機構情報・計算工学センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構情報・計算工学センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構情報・計算工学センター | ||||||
著者所属(英) | ||||||
en | ||||||
JAXA's Engineering Degital Innovation Center, Japan Aerospace Exploration Agency (JAXA)(JEDI) | ||||||
著者所属(英) | ||||||
en | ||||||
JAXA's Engineering Degital Innovation Center, Japan Aerospace Exploration Agency (JAXA)(JEDI) | ||||||
著者所属(英) | ||||||
en | ||||||
JAXA's Engineering Degital Innovation Center, Japan Aerospace Exploration Agency (JAXA)(JEDI) | ||||||
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) | |||||
書誌情報 |
宇宙輸送シンポジウム: 講演集録 en : Proceedings of Space Transportation Symposium 巻 平成21年度, 発行日 2010-01 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部) | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | To improve rocket engine performance, mass flow rate of turbine driving gas should be small, especially for an open cycle liquid rocket engine. However, work output must be high as possible. As a result, pressure ratio of the turbine becomes high and Mach number at both nozzle exit and rotor inlet becomes supersonic. Therefore strong shockwave interaction can be generated between nozzle exits and rotor inlet, and this interaction affects the turbine aerodynamic performance. However this rotor-stator interaction of supersonic turbine has not yet been clarified. To evaluate such numerical approach, in the present study, quasi 2D RANS simulations were applied to the NACA supersonic turbine and the numerical results were compared with the experimental results. The flow field between nozzle and rotor region and the turbine isentropic efficiency were investigated. RANS models and nozzle/rotor interface modeling method were compared, and its impact to the turbine aerodynamic performance was evaluated. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: CD-ROM1枚 | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Note: One CD-ROM | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10324301 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064741013 |