JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
65515000.pdf1.21 MB
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
Other TitleParameter Study on Blade Losses of a Rocket Turbopump Turbine
Author(jpn)瀧田, 純也; 福田, 太郎; 宇山, 遼一; 船﨑, 健一; 内海, 政春
Author(eng)Takida, Junya; Fukuda, Taro; Uyama, Ryoichi; Funazaki, Kenichi; Uchiumi, Masaharu
Author Affiliation(jpn)宇宙航空研究開発機構宇宙輸送ミッション本部宇宙輸送系推進技術研究開発センターエンジン研究開発グループ(JAXA); 第一システムエンジニアリング 第3技術部; 第一システムエンジニアリング 第3技術部; 岩手大学工学部; 宇宙航空研究開発機構宇宙輸送ミッション本部宇宙輸送系推進技術研究開発センターエンジン研究開発グループ(JAXA)
Author Affiliation(eng)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)
Issue Date2013-01-31
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA Rresearch and Development Memorandum
VolumeJAXA-RM-12-008
Start page1
End page9
Publication date2013-01-31
Languagejpn
eng
AbstractDue 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.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsAMDC+KO Loss Model; Blade Aspect Ratio; Craig & Cox Loss Model; Zweifel factor
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0065515000
Report NoJAXA-RM-12-008
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/20565


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