JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63736000.pdf2.61 MB
Other TitleOn the compact design of rocket engine turbopump
Author(jpn)吉田 義樹; 渡辺 啓悦
Author(eng)Yoshida, Yoshiki; Watanabe, Hiroyoshi
Author Affiliation(jpn)宇宙航空研究開発機構 宇宙基幹システム本部 宇宙輸送系推進技術研究開発センター; 荏原総合研究所
Author Affiliation(eng)Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations; Ebara Research Co. Ltd.
Issue Date2007-12-28
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2007-12-28
AbstractInvestigation on compact design of rocket pump impeller and diffuser by using inverse design was presented. Two compact sizing, 95 percent and 90 percent of original design based on impeller and diffuser exit radius were investigated in this study. The performances and internal flow fields in the inverse designed impellers and diffusers were evaluated by Computational Fluid Dynamics (CFD) technique. The CFD results show the flow non-uniformity at the impeller exit tends to be increased from increased blade loading of compact design. The compact sizing of 90 percent of original design shows large penalty in performance at the 94 percent design flow by diffuser stall. The compact sizing 95 percent of original design showed a small performance penalty to original design in the range of 94 percent to 106 percent design flow rate, however impeller performance improvement compatible to the original design was expected by adopting wider impeller exit width and blade staking.
DescriptionJAXA Research and Development Memorandum
Keywordsrocket engine design; pump impeller; turbopump; inverse design; computational fluid dynamics; computational grid; liquid oxygen; flow distribution; wake; design optimization; ロケットエンジン設計; ポンプインペラ; ターボポンプ; 逆解法設計; 計算流体力学; 計算格子; 液体酸素; 流れの分布; 後流; 設計最適化
Document TypeTechnical Report
JAXA Category研究開発資料
Report NoJAXA-RM-07-005

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