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Simulation of a compressor cascade with stalled flow using Large Eddy Simulation with two-layer approximate boundary conditions

机译:使用两层近似边界条件的大涡模拟对具有停滞流的压缩机叶栅进行模拟

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The final objective of the study is to provide correlations and models, which are able to describe axial compressor behaviour in some particular incidental or accidental conditions, such as stall. The present contribution consists to establish and begin to validate numerical simulations by comparison with representative experimental data on a planar static compressor cascade. Trio_U software is used to perform Large Eddy Simulations with a standard wall-function (SWF) or a two-layer approximate boundary conditions (TBLE). The results obtained show a good behaviour of the TBLE model compared to an open literature case of the gas turbine aircraft community. Sensitivity studies are performed on various parameters (solidity, angle of incidence) and take part of a database.
机译:该研究的最终目的是提供相关性和模型,它们能够描述在某些特定的偶然或偶然条件下(例如失速)的轴向压缩机行为。本贡献包括通过与平面静态压缩机叶栅上的代表性实验数据进行比较来建立并开始验证数值模拟。 Trio_U软件用于执行具有标准壁函数(SWF)或两层近似边界条件(TBLE)的大涡模拟。与燃气涡轮飞机社区的公开文献案例相比,获得的结果表明TBLE模型具有良好的性能。敏感性研究是针对各种参数(固体,入射角)进行的,并纳入了数据库。

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