A Computational Methodology for Large-Eddy Simulation of Tip-Clearance Flows
A Computational Methodology for Large-Eddy Simulation of Tip-Clearance Flows
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DOI：
10.1115/fedsm2003-45395
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发表时间：
2003
期刊：
影响因子：
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通讯作者：
D. You;R. Mittal;Meng Wang;P. Moin
中科院分区：
文献类型：
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作者：
D. You;R. Mittal;Meng Wang;P. Moin
发展了一种浸没边界技术与曲线结构网格相结合的大涡模拟(LES)求解器，用于研究不可压缩旋翼叶顶间隙流动的时间和空间动力学。这些模拟的总体目标是确定转子下游靠近端壁的低压波动的潜在机制。讨论了数值方法的显著特点，包括网格拓扑结构、浸没边界方法、在高斜度网格上处理无耗散格式的数值不稳定性以及共享内存平台的代码并行化。计算结果表明，该方法能够很好地模拟以不同叶片相关涡结构与湍流端壁边界层相互作用为特征的高度复杂的流场演变过程。将模拟结果与实验结果进行了比较，定性和定量结果都是一致的。版权所有©2003 by ASME
A large-eddy simulation (LES) solver which combines an immersed-boundary technique with a curvilinear structured grid has been developed to study the temporal and spatial dynamics of an incompressible rotor tip-clearance flow. The overall objective of these simulations is to determine the underlying mechanisms for low-pressure fluctuations downstream of the rotor near the endwall. Salient features of the numerical methodology, including the mesh topology, the immersed boundary method, the treatment of numerical instability for non-dissipative schemes on highly skewed meshes, and the parallelization of the code for shared memory platforms are discussed. The computational approach is shown to be capable of capturing the evolution of the highly complicated flowfield characterized by the interaction of distinct blade-associated vortical structures with the turbulent endwall boundary layer. Simulation results are compared with experiments and qualitative as well as quantitative agreement is observed.Copyright © 2003 by ASME