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Analysis of Inlet-Compressor Acoustic Interactions Using Coupled CFD Codes

机译:使用耦合CFD代码分析入口-压缩机的声学相互作用

摘要

A problem that arises in the numerical simulation of supersonic inlets is the lack of a suitable boundary condition at the engine face. In this paper, a coupled approach, in which the inlet computation is coupled dynamically to a turbomachinery computation, is proposed as a means to overcome this problem. The specific application chosen for validation of this approach is the collapsing bump experiment performed at the University of Cincinnati. The computed results are found to be in reasonable agreement with experimental results. The coupled simulation results could also be used to aid development of a simplified boundary condition.
机译:在超音速进气道的数值模拟中出现的问题是在发动机表面缺乏合适的边界条件。在本文中,提出了一种将进气道计算动态地耦合到涡轮机械计算的耦合方法,作为克服此问题的一种手段。选择用于验证这种方法的特定应用是在辛辛那提大学进行的坍塌碰撞实验。计算结果与实验结果合理吻合。耦合的仿真结果也可以用于帮助简化边界条件的开发。

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