G606 ロケットエンジン用ターボポンプ主羽根車小径化に関する検討(2)(GS-6-2 翼干渉,フィン,境界層,一般セッション)

概要

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Investigation on compact design of rocket pump impeller and diffuser by using inverse deign was presented. Two compact sizing, 95% and 90% 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% of original design shows large penalty in performance at the 94% design flow by diffuser stall. The compact sizing 95% of original design showed a small performance penalty to original design in the range of 94% to 106% design flow rate, however impeller performance improvement compatible to the original design was expected by adopting wider impeller exit width.
2006-10-28