Modelling of Film Cooling for Turbine Blade Design
Modelling of Film Cooling for Turbine Blade Design
复制标题
涡轮叶片设计的气膜冷却建模
DOI：
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发表时间：
2008
期刊：
影响因子：
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通讯作者：
C. Hirsch
中科院分区：
文献类型：
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作者：
B. Tartinville;C. Hirsch
现代涡轮机叶片设计中使用计算流体动力学，要求精确表示气膜冷却的效果。然而，包括在计算域中的冷却孔需要大量的网格划分工作，并导致计算时间急剧增加。因此，本文提出在冷却孔出口处加入一个局部源项来表示冷却孔的影响。这种方法的主要优点是，它不需要任何额外的网格划分工作，并导致只有一个小的增加计算时间。用这种方法得到的结果进行比较，实验数据和一系列的测试情况下的冷却孔的全啮合得到的结果。虽然不能完全捕捉孔下游的流动结构的细节，但这种方法可以准确预测冷却孔的存在引起的整体流动和性能变化。Copyright © 2008 by NUMECA
The use of Computational Fluid Dynamics for modern turbine blade design requires the accurate representation of the effect of film cooling. However, including the cooling holes in the computational domain requires a substantial meshing effort and leads to a drastic increase in the computing time. Therefore, it is here proposed to represent the effect of cooling holes by adding a local source term at the hole exit. The major advantage of such a method is that it does not require any additional meshing effort and induces only a small increase in computational time. Results obtained with this approach are compared to experimental data and to results obtained with the full meshing of the cooling holes on a series of test cases. Though details of the flow structure downstream of the holes cannot be perfectly captured, this method allows an accurate prediction of the overall flow and performance modifications induced by the presence of the cooling holes.Copyright © 2008 by NUMECA