Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
IHI
Yokohama National University
出版者
宇宙航空研究開発機構
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-11-017
ページ
1 - 8
発行年
2012-03-30
抄録（英）
In a rocket turbopump, an axial thrust balancing system with the balance piston is often applied to reduce the axial thrust. The leakage flow through the balance piston is affected by the configuration of the balance piston and the balancing point in the axial direction. In designing the internal flow system, the balancing point and flow rate have been estimated by the static analysis code of the internal flow. On the other hand, the analysis code for dynamic response of the internal flow through the balance piston was developed. In this study, optimal calculation considering the axial dynamic characteristics of the internal flow system was carried out by using the dynamic analysis code. As the results, the balancing point in the steady state significantly affects the leakage flow rate and the axial vibration.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
軸方向の動特性を考慮したロケット用ポンプ内部流路の最適設計
65215000.pdf
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