Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
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特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004
巻
JAXA-SP-04-012
ページ
160 - 165
発行年
2005-03-25
抄録（英）
The fuel turbo pump (FTP) of LE-7A engine had vibration problem of turbine rotor system. The turbine consists of 33 nozzle vanes, 58 rotor blades, 36 stator vanes and an upstream manifold. The manifold has 30 radial slits between a volute and a downstream passage. It was important to clarify the cause of the turbine rotor vibration. Therefore, CFD was applied to investigate internal flow field and to obtain aerodynamic characteristics of the turbine. The turbine cascade part and the upstream manifold part were simulated separately, in this study. In the turbine cascade simulation, the effect of rotor tip leakage flow was investigated. As a result of the numerical calculation, it was assumed that the change of tip clearance in accordance with the eccentricity of turbine rotor reduce the system dump of the rotor system. On the other hand, the manifold simulation shows unsteady flow phenomena downstream of the slits. Analysis and visualization of numerical simulation results revealed the unsteady flow caused by periodical vortex shedding from the wake of the manifold struts.
LE-7Aエンジンタービン流れの数値シミュレーション
48469027.pdf
(2.54MB)
