跨音压气机中非结构网格自适应的研究
发布时间：2018-11-16 11:51
【摘要】：跨音压气机中存在激波/边界层相互干涉、激波/叶尖泄漏涡相互干涉等复杂流动结构,为了实现高精度的数值模拟,精细的捕捉到激波以及叶尖泄漏涡附近的流动结构,从而探究其复杂的流动机理,本文发展了非结构网格自适应技术,其可以自动的加密关注流动特征附近的网格,从而实现对激波、叶尖泄漏涡及激波与其他流动现象相互作用的流动结构的精细捕捉。本文将网格自适应技术应用于RAE-2822翼型二维激波算例以及真实跨音速压气机Rotor-37算例的数值模拟中,计算结果表明网格自适应技术能自动的捕捉到激波、叶尖泄漏涡及其与其他流动现象相互干涉的精细流动结构。
[Abstract]:There are complex flow structures such as shock wave / boundary layer interaction, shock wave / tip leakage vortex interference and so on in transonic compressor. In order to achieve high accuracy numerical simulation, the shock wave and the flow structure near the tip leakage vortex can be accurately captured. In order to explore its complex flow mechanism, this paper develops the unstructured mesh adaptive technology, which can automatically encrypt and pay attention to the grid near the flow characteristics, so as to realize the shock wave. Fine capture of tip leakage vortices and shock waves interacting with other flow phenomena. In this paper, the grid adaptive technique is applied to the numerical simulation of 2D shock wave of RAE-2822 airfoil and Rotor-37 example of real transonic compressor. The results show that the grid adaptive technique can capture shock wave automatically. Tip leakage vortex and its fine flow structure which interferes with other flow phenomena.
【作者单位】： 清华大学热科学与动力工程教育部重点实验室;
【基金】：国家自然科学基金重点项目(No.51136003);国家自然科学基金青年项目(No.51506107)
【分类号】：TH45
本文编号：2335441
[Abstract]:There are complex flow structures such as shock wave / boundary layer interaction, shock wave / tip leakage vortex interference and so on in transonic compressor. In order to achieve high accuracy numerical simulation, the shock wave and the flow structure near the tip leakage vortex can be accurately captured. In order to explore its complex flow mechanism, this paper develops the unstructured mesh adaptive technology, which can automatically encrypt and pay attention to the grid near the flow characteristics, so as to realize the shock wave. Fine capture of tip leakage vortices and shock waves interacting with other flow phenomena. In this paper, the grid adaptive technique is applied to the numerical simulation of 2D shock wave of RAE-2822 airfoil and Rotor-37 example of real transonic compressor. The results show that the grid adaptive technique can capture shock wave automatically. Tip leakage vortex and its fine flow structure which interferes with other flow phenomena.
【作者单位】： 清华大学热科学与动力工程教育部重点实验室;
【基金】：国家自然科学基金重点项目(No.51136003);国家自然科学基金青年项目(No.51506107)
【分类号】：TH45
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，本文编号：2335441
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