並列タイトル等Numerical Flow Analysis for Axial Flow Turbine
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-3
一般注記Some numerical flow analysis methods adopted in the gas turbine interactive design system, TDSYS, are described. Recently, computer aided design systems which enable designers to achieve better design in a shorter period have been introduced into the field of turbomachinery design. Numerical flow analysis programs have been incorporated into the aerodynamic part of the system and have greatly facilitated sophisticated aerodynamic design methods. In the TDSYS, a streamline curvature program for axisymmetric flows, quasi 3-D and fully 3-D time marching programs are used respectively for blade to blade flows and annular cascade flows. The streamline curvature method has some advantages in that it can include the effect of coolant mixing and choking flow conditions. Comparison of the experimental results with calculated results shows that the overall accuracy is determined more by the empirical correlations used for loss and deviation than by the numerical scheme. The time marching methods are the best choice for the analysis of turbine cascade flows because they cart handle mixed subsonic-supersonic flows with automatic inclusion of shock waves in a single calculation. Some experimental results show that a time marching method can predict the airfoil surface Mach number distribution more accurately than a finite difference method. One weakpoint of the time marching methods is a long computer time; they usually require several times as much CPU time as other methods. But reductions in computer costs and improvements in numerical methods have made the quasi 3-D and fully 3-D time marching methods usable as design tools, and they are now used in TDSYS.
資料番号: NALSP0003014
レポート番号: NAL SP-3
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ