Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Engine System Research and Development Group, Space Transportation Propulsion Research and Development Center, Space Transportation Mission Directorate, Japan Aerospace Exploration Agency (JAXA)
Faculty of Engineering, Iwate 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-11-011
ページ
1 - 7
発行年
2012-02-24
抄録（英）
An application of robust design process for reduction in Thomas force of rocket turbopump turbines is presented in this paper．Because of its special specification, rocket turbopump turbines are designed as supersonic impulse turbines, and as a result, these blades have higher loading．In such a high loading blade, there is a possibility of rotor vibration problem generated by turbine instability force, that is, "Thomas Force"．Actually in the past engine development in Japan, there was the shaft vibration problem due to "Thomas Force"．In order to reduce shaft vibrations, it is important to keep "Thomas Force" small．In this paper, the results of parametric design for the existing rocket turbopump turbine by using the robust design process are discussed.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
ロバスト設計手法を用いたターボポンプ用タービンのトーマスフォース低減
65209000.pdf
(2.05MB)
