Abstract A mesh adaptation methodology for wall-modeled turbomachinery Large Eddy Simulation (LES) is proposed, simultaneously taking into account two quantities of interest: the average kinetic energy dissipation rate and the normalized wall distance y + . This strategy is first tested on a highly loaded transonic blade with separated flow, and is compared to wall-resolved LES results, as well as experimental data. The adaptation methodology allows to predict fairly well the boundary layer transition on the suction side and the recirculation bubble of the pressure side. The method is then tested on a real turbofan stage for which it is shown that the general operating point of the computation converges toward the experimental one. Furthermore, comparison of turbulence predictions with hot-wire anemometry show good agreement as soon as a first adaptation is performed, which confirms the efficiency of the proposed adaptation method.

中文翻译：

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复杂壁面建模涡轮机械 LES 的网格自适应策略

摘要 提出了一种壁面建模涡轮机械大涡模拟 (LES) 的网格自适应方法，同时考虑了两个感兴趣的量：平均动能耗散率和归一化壁面距离 y + 。该策略首先在具有分离流的高负载跨音速叶片上进行测试，并与壁分辨 LES 结果以及实验数据进行比较。适应方法允许相当好地预测吸入侧的边界层过渡和压力侧的再循环气泡。然后在真实的涡轮风扇级上对该方法进行测试，结果表明计算的一般操作点向实验点收敛。此外，