【摘要】：跨音壓氣機中存在激波/邊界層相互干涉、激波/葉尖泄漏渦相互干涉等復雜流動結構,為了實現高精度的數值模擬,精細的捕捉到激波以及葉尖泄漏渦附近的流動結構,從而探究其復雜的流動機理,本文發(fā)展了非結構網格自適應技術,其可以自動的加密關注流動特征附近的網格,從而實現對激波、葉尖泄漏渦及激波與其他流動現象相互作用的流動結構的精細捕捉。本文將網格自適應技術應用于RAE-2822翼型二維激波算例以及真實跨音速壓氣機Rotor-37算例的數值模擬中,計算結果表明網格自適應技術能自動的捕捉到激波、葉尖泄漏渦及其與其他流動現象相互干涉的精細流動結構。
[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.
【作者單位】： 清華大學熱科學與動力工程教育部重點實驗室;
【基金】：國家自然科學基金重點項目(No.51136003);國家自然科學基金青年項目(No.51506107)
【分類號】：TH45

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