This study aims at evaluating the feasibility and the accuracy of a Wall-Modeled Large Eddy Simulation of an actual aeronautical multistage axial high-pressure compressor. The computational domain is composed of 37 blades and a geometrically complex recirculating cavity. The numerical method TurboAVBP is able to handle such a technical challenge thanks to its unstructured and massively parallel approach as well as dedicated rotor-stator interface treatments. The influence of grid resolution, from less than 100 millions to more than 1 billion of cells, is particularly evaluated. The intermediate grid correctly predicts the global aerodynamic performances up to the lowest mass flow rate regime. In comparing with time-resolved measurements, the finest grid is shown to accurately predict flow within rotors, especially in their tip regions that are critical for performances and stability of the whole compressor.

中文翻译：

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多级高压压缩机的壁面建模大涡模拟

本研究旨在评估实际航空多级轴向高压压缩机的壁面模型大涡模拟的可行性和准确性。计算域由 37 个叶片和一个几何复杂的循环腔组成。由于其非结构化和大规模并行方法以及专用的转子 - 定子界面处理，数值方法 TurboAVBP 能够应对这样的技术挑战。特别评估了网格分辨率的影响，从不到 1 亿个到超过 10 亿个单元格。中间网格正确预测了最低质量流率状态下的全球空气动力学性能。与时间分辨测量相比，最好的网格被证明可以准确预测转子内的流量，