Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Third Engineering Department, Daiichi System Engineering
Third Engineering Department, Daiichi System Engineering
Faculty of Engineering, Iwate University
Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
出版者
宇宙航空研究開発機構(JAXA)
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構研究開発資料
雑誌名(英)
JAXA Research and Development Memorandum
巻
JAXA-RM-12-008
ページ
1 - 9
発行年
2013-01-31
抄録（英）
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.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
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
65515000.pdf
(1.24MB)
