numerical simulation, turbine blade, film cooling, thermodynamic efficiency, high temperature, gas turbine engine, aerodynamic characteristic, temperature distribution, air cooling, research and development, Reynolds averaging, Navier-Stokes equation
その他のタイトル（英）
Numerical simulation of the flow in a film-cooled turbine blade row
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: 航空宇宙数値シミュレーション技術シンポジウム2002論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002
巻
57
ページ
238 - 243
発行年
2003-03
抄録（英）
The computation is performed on a turbine stator blade with cooling air ejection from multi-row holes on the surface. This computation reveals the complicated three-dimensional structure in the stator passage including secondary flow and end-wall separation, and how the ejected cooling air flows on the blade surface and how the surface temperature is protected from the hot gas. The influence of the air ejection on the aerodynamic performance is also examined.
フィルム冷却されたタービン翼列内流れの数値シミュレーション
nalsp0057042.pdf
(2.83MB)
