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以S系列新翼型为例,针对设计风速最佳攻角含有叶尖涡的复杂流动,提出一种采用分区域过渡层网格的方法来改善叶尖涡模拟的新网格生成策略。这种利用过渡层网格从叶片的贴体网格区域向中部加密网格区域中捕捉叶尖涡形成的位置和大小,通过控制网格梯度变化能获得高精度计算结果。数值计算和分析表明:该网格能合理捕捉到S系列新翼型叶尖涡的细节变化信息以及叶轮表面压力分布的细节变化特性,发现了风力机叶尖涡在初期向内迁移的现象。证明该网格生成策略合理有效。
Taking S series new airfoils as an example, aiming at the complicated flow with the tip vortex at the best angle of attack, a new mesh generation strategy is proposed to improve the simulation of the tip vortex by using the sub-region transition mesh method. This transition layer grid captures the position and size of tip vortices from the body-fitted grid region of the blade to the middle-scaled grid region, and high-precision calculation results can be obtained by controlling the grid gradient changes. Numerical calculation and analysis show that the grid can reasonably capture the detail change information of blade tip vortex and the details of the pressure distribution on the surface of the impeller. It is found that the tip vortex migrates inward at the initial stage. Prove that the grid generation strategy is reasonable and effective.