Gas turbine film cooling
Gas turbine film cooling
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DOI：
10.2514/1.18034
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发表时间：
2006-03-01
影响因子：
1.9
通讯作者：
Thole, KA
中科院分区：
文献类型：
--
作者：
Bogard, DG;Thole, KA
燃气涡轮发动机的耐久性很大程度上取决于部件的温度。对于燃烧室和涡轮翼型和端壁，气膜冷却被广泛用于降低部件温度。气膜冷却是当今几乎所有飞机涡轮发动机和许多发电涡轮发动机中使用的一种冷却方法，但存在非常难以预测的现象。横流中射流的相互作用是膜状冷却的代表，它产生剪切层，导致表面混合和冷却性能衰减。这种相互作用高度依赖于射流与横流的质量和动量通量比。由于涡轮发动机翼型部件表面固有的复杂流场，导致气膜冷却性能难以预测。薄膜冷却应用于几乎所有与暴露于热燃烧气体的翼型相关的外表面，如前缘、主体、叶片尖端和端壁。在文献综述中，我们发现自由流湍流、表面曲率和孔形状对膜冷却性能有很强的影响。通过对分析方法的讨论、物理描述以及对膜冷却性能的各种影响，对膜冷却进行了回顾。
The durability of gas turbine engines is strongly dependent on the component temperatures. For the combustor and turbine airfoils and endwalls, film cooling is used extensively to reduce component temperatures. Film cooling is a cooling method used in virtually all of today's aircraft turbine engines and in many power-generation turbine engines and yet has very difficult phenomena to predict. The interaction of jets-in-crossflow, which is representative of film cooling, results in a shear layer that leads to mixing and a decay in the cooling performance along a surface. This interaction is highly dependent on the jet-to-crossflow mass and momentum flux ratios. Film-cooling performance is difficult to predict because of the inherent complex flowfields along the airfoil component surfaces in turbine engines. Film cooling is applied to nearly all of the external surfaces associated with the airfoils that are exposed to the hot combustion gasses such as the leading edges, main bodies, blade tips, and endwalls. In a review of the literature, it was found that there are strong effects of freestream turbulence, surface curvature, and hole shape on the performance of film cooling. Film cooling is reviewed through a discussion of the analyses methodologies, a physical description, and the various influences on film-cooling performance.