跨音速
多重网格法
离散化
机械
失速(流体力学)
平滑的
数学
缩放比例
计算流体力学
计算机科学
物理
数学分析
几何学
空气动力学
偏微分方程
统计
出处
期刊:Journal of turbomachinery
[ASME International]
日期:1994-07-01
卷期号:116 (3): 435-445
被引量:191
摘要
A three-dimensional code for rotating blade-row flow analysis has been developed. The space discretization uses a cell-centered scheme with eigenvalue scaling for the artificial dissipation. The computational efficiency of a four-stage Runge–Kutta scheme is enhanced by using variable coefficients, implicit residual smoothing, and a full-multigrid method. An application is presented for the NASA rotor 67 transonic fan. Due to the blade stagger and twist, a zonal, nonperiodic H-type grid is used to minimize the mesh skewness. The calculation is validated by comparing it with experiments in the range from the maximum flow rate to a near-stall condition. A detailed study of the flow structure near peak efficiency and near stall is presented by means of pressure distribution and particle traces inside boundary layers.
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