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A comperative experimental study between the film effectiveness of trench and diffusion film holes
International Journal of Thermal Sciences ( IF 4.5 ) Pub Date : 2021-03-01 , DOI: 10.1016/j.ijthermalsci.2020.106713
Sainathkaushik Balaji , Fan Yang , Mohammad E. Taslim

Abstract Gas turbine airfoils have been consistently exposed to very high temperature gases to extract maximum power. Therefore, there is a growing need to protect the airfoil surfaces from the potentially surface damaging high temperature gases. Film cooling holes and trenches are one possible solution to the aforementioned problem. This thermal protection scheme which has been in practice for some considerable time, is an active area for optimization and will be our major theme of this research paper. Trenches as the name suggests are troughs on the surfaces to be cooled that are constantly filled with the coolant. The cooling air is carried over the hot surfaces by the passing hot gases to create a thin blanket over the surface. In order to achieve the best possible coolant spread over the hot surfaces, a new trench geometry that combines the positives of a slanted circular feed hole and a multi-sided trench has been adopted in this study. That geometry with its axis parallel to the flow direction served as our baseline geometry. The second geometry was identical to the baseline in all aspects except that the trenches and feed holes were rotated about the normal to the test plate by 30° to create a compound-angle-trench. The third geometry was a 7o-7o-7o diffusion hole. Pressure Sensitive Paint (PSP) technique was utilized to test these geometries for their film cooling effectiveness. Major conclusions of this study are: a) The streamwise as well as spanwise coverage of trench geometries are superior to those of 7-7-7 diffusion holes, b) The compound-angle-trench geometry produced the highest film effectiveness in both streamwise and spanwise directions and c) the blowing ratio of 1 was found to be the optimum value for the best streamwise and spanwise film effectiveness distribution.

中文翻译:

沟槽与扩散膜孔的成膜效能对比实验研究

摘要 燃气轮机翼型件一直暴露在非常高温的气体中以获取最大功率。因此,越来越需要保护翼型表面免受潜在的表面破坏性高温气体的影响。薄膜冷却孔和沟槽是上述问题的一种可能的解决方案。这种热保护方案已经实践了相当长的一段时间,是一个活跃的优化领域,将是我们本研究论文的主要主题。顾名思义,沟槽是要冷却的表面上不断充满冷却剂的槽。冷却空气被通过的热气体带到热表面上,在表面上形成一层薄薄的毯子。为了在热表面上获得尽可能好的冷却剂,本研究采用了一种新的沟槽几何形状,它结合了倾斜圆形进料孔和多边沟槽的优点。其轴平行于流动方向的几何图形作为我们的基线几何图形。第二个几何形状在所有方面都与基线相同,除了沟槽和进料孔围绕测试板的法线旋转 30° 以创建复合角沟槽。第三个几何形状是一个 7o-7o-7o 的扩散孔。使用压敏涂料 (PSP) 技术来测试这些几何形状的薄膜冷却效果。本研究的主要结论是: a) 沟槽几何形状的流向和展向覆盖率优于 7-7-7 扩散孔,
更新日期:2021-03-01
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