Improved Prediction of Turbomachinery Flows Using Near-Wall Reynolds-Stress Model
Improved Prediction of Turbomachinery Flows Using Near-Wall Reynolds-Stress Model
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DOI：
10.1115/1.1426083
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发表时间：
2001-06
影响因子：
1.7
通讯作者：
G. Gerolymos;J. Neubauer;V. Sharma;I. Vallet
中科院分区：
文献类型：
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作者：
G. Gerolymos;J. Neubauer;V. Sharma;I. Vallet
本文试图用一种新的近壁涡壳-应力模型来评价复杂涡壳流预测的改进。湍流闭合是一个近壁低湍流数的湍流应力模型，它独立于离壁的距离和垂直于壁的方向。该模型考虑了科氏力重分布对残余应力的影响。使用隐式耦合O（Δx 3）逆风偏置求解器求解五个平均流方程和七个湍流模型方程。将结果与三种涡轮构型的实验数据进行了比较：NTUA高亚音速环形叶栅、NASA-37转子和RWTH 1 1/2级涡轮机。给出了详细的流场分析。可以看出，新模型，考虑到的奥尔兹应力各向异性大大提高了与实验数据的一致性，特别是对于大分离的流动，而只有30%的成本比k-e模型（由于一个有效的隐式实现）。人们相信，先进湍流模型的进一步研究将大大提高复杂湍流的预测能力在湍流。
In this paper an assessment of the improvement in the prediction of complex turbomachinery flows using a new near-wall Reynolds-stress model is attempted. The turbulence closure used is a near-wall low-turbulence-Reynolds-number Reynolds-stress model, that is independent of the distance-from-the-wall and of the normal-to-the-wall direction. The model takes into account the Coriolis redistribution effect on the Reynolds-stresses. The five mean flow equations and the seven turbulence model equations are solved using an implicit coupled O(Δx 3 ) upwind-biased solver. Results are compared with experimental data for three turbomachinery configurations: the NTUA high subsonic annular cascade, the NASA―37 rotor, and the RWTH 1 1/2 stage turbine. A detailed analysis of the flowfield is given. It is seen that the new model that takes into account the Reynolds-stress anisotropy substantially improves the agreement with experimental data, particularily for flows with large separation, while being only 30 percent more expensive than the k-e model (thanks to an efficient implicit implementation). It is believed that further work on advanced turbulence models will substantially enhance the predictive capability of complex turbulent flows in turbomachinery.