@inproceedings{oai:jaxa.repo.nii.ac.jp:00016583,
 author = {河津, 要 and 谷, 直樹 and 山西, 伸宏 and Kawatsu, Kaname and Tani, Naoki and Yamanishi, Nobuhiro},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {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), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, 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., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0064741013},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {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},
 volume = {平成21年度},
 year = {2010}
}