用高效矢通量分裂格式求解二维叶栅的跨音流动  

HEAT TRANSFER FROM SHROUDED ROTATING DISK WITH CENTRIC AIR INFLOW

作　　者：刘慎之[1] 刘斌[1] 向一敏[1] 

机构地区：[1]西安交通大学

出　　处：《航空动力学报》1994年第1期24-26,共3页Journal of Aerospace Power

基　　金：国家自然科学基金

摘　　要：提出了一种高效隐式矢通量分裂格式。该格式通过在显格式上添加合适的高阶小量，避免了近似因子分解和系数矩阵运算，大大地减少了计算量。同时该格式在收敛性及激波捕捉精度等方面均保持了矢通量分裂格式所具有的优势。将该格式用到了二维叶栅的无粘跨音流场的数值模拟中去，结果令人满意，证实了无矩阵运算、无近似因子分解的隐格式构造有一定的推广意义。Abstract An air cooled turbine disk was investigated as the model of a rotating disk near a shrouded stator with centric inflow of cooling air.The heat transfer performance of the rotating disk was experimentally studied in consideration of rotational Reynolds number Re、mass flow coefficient C w、gap ratio G and shrouded clearance ratio G s.The disk diameter is 360mm and its maximal rotational speed is 3600rpm.The disk was electrically heated at the outer radial side.One of the disk surfaces was cooled by air and the another surface was adiabatic.Temperature of heated side and cooled surface was measured.Mean Nusselt number of cooled surface has been obtained by using numerical method.For large Reynolds number,the mean Nusselt number is slightly affected by the Reynolds number.Increasing mass flow coefficient can enhance the capacity of heat transfer.The effects of G and G s are small.An emperical correlation of the heat transfer coefficient of rotating disk is proposed.

关 键 词：叶栅 跨音速流动 数值模拟 激波 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]