軸流圧縮機翼列流れの非圧縮性粘性流解析 : 格子形状の選択と計算結果への影響)

概要

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In the present work, incompressible high Reynold's number flows around a compressor blade cascade at low speeds (Mach number 0.25) are analyzed by solving the N-S equations using the finite difference method. A generalized coordinate system is used so that a sufficient number of grid points are distributed in the boundary layer and in the wake region. A third-order upwind scheme is used for the convective term, which suppresses the non-linear instability for calculation of the high Reynold's number flow used in the present computation. The experimental-flow Reynold's number defined on the basis of blade chord length and cascade inlet velocity is 7×10^5. Grid topology is thought to be as important as flow solver, therefore calculations are carried out using H-type and C type grids and the results of the calculations are compared with the experimental data obtained for a controlled diffusion-type axial compressor rotor blade cascade for three different inlet flow conditions, which included design and off-design conditions. The study led to a clear understanding of the importance of the grid topology on the prediction of experimental flow behavior.
社団法人日本機械学会の論文
1995-11-25