Ishikawajima-Harima Heavy Industries Co Ltd
Ishikawajima-Harima Heavy Industries Co Ltd
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
37
ページ
23 - 28
発行年
1998-02
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 12-13 Jun. 1997 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan
A three-dimensional time-accurate Reynolds-averaged Navier-Stokes code has been extended for use in a parallel supercomputer called Numerical Wind Tunnel (NWT) developed by the Japanese National Aerospace Laboratory. The power of parallel supercomputer enables to perform a more accurate computation of the unsteady flowfield within a multipassage configuration. The first step was to validate the CFD (Computational Fluid Dynamics) results using the experimental measurements of the stator-rotor configuration of a high pressure turbine. The CFD results also explained the flow mechanism appeared at the exit of the rotor. The second step was to investigate the flowfield with hot streak inflow of the high pressure turbine. Introduction of hot streaks in the analysis showed the effects of the relative circumferential positions on the hot streak distributions through the turbine stage, and also showed some features of temperature fluctuations on the rotor blade surface.
航空機エンジン内の3次元非定常流れ解析
nalsp0037003.pdf
(1.83MB)
