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Bibliographic Record
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- Material Type
- 規格・テクニカルリポート類
- Author/Editor
- 瀧田, 純也福田, 太郎宇山, 遼一船﨑, 健一内海, 政春Takida, JunyaFukuda, TaroUyama, RyoichiFunazaki, KenichiUchiumi, Masaharu
- Author Heading
- Publication, Distribution, etc.
- Publication Date
- 2013-01-31
- Publication Date (W3CDTF)
- 2013-01-31
- Alternative Title
- Parameter Study on Blade Losses of a Rocket Turbopump Turbine
- Periodical title
- 宇宙航空研究開発機構研究開発資料
- No. or year of volume/issue
- JAXA-RM-12-008
- Volume
- JAXA-RM-12-008
- Pages
- 1-9
- ISSN (Periodical Title)
- ISSN : 1349-1121
- Text Language Code
- jpn
- Target Audience
- 一般
- Note (General)
- 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
- Access Restrictions
- インターネット公開
- Periodical Title (NCID)
- AA11983593
- Data Provider (Database)
- 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
- Original Data Provider (Database)
- 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ