@techreport{oai:jaxa.repo.nii.ac.jp:00002524,
 author = {瀧田, 純也 and 福田, 太郎 and 宇山, 遼一 and 船﨑, 健一 and 内海, 政春 and Takida, Junya and Fukuda, Taro and Uyama, Ryoichi and Funazaki, Kenichi and Uchiumi, Masaharu},
 month = {Jan},
 note = {Due to its special specification, rocket turbopump turbine blades have higher loading and its aspect ratio is extremely low. In such a situation, it is difficult to predict turbine efficiency accurately in system design phase of rocket engine. The purpose of the present work is to evaluate the accuracy of existing one dimensional loss model. By using the steady three dimensional CFD analyses, parametric studies against the major design variables such as tip clearance, blade loading, blade aspcet ratio, were carried out. These simulation results were compared with the results that were also obtained by using the existing one dimensional loss models. The results clarified the cause of the reduction of accuracy of one-dimensional prediction of turbine efficiency. The one-dimensional loss model was found to underestimate the loss under the condition of a blade with a low aspect ratio. From comparison between the existing one-dimensional loss models, it was also found that the "Craig & Cox model" could reproduce the tendency for blade loading correctly., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065515000, レポート番号: JAXA-RM-12-008},
 title = {ロケットターボポンプ用タービンの翼損失に関するパラメータスタディ},
 year = {2013}
}