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首页> 外文期刊>Journal of Heat Transfer >Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes
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Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes

机译：低压涡轮叶片前缘冲击冷却系统传热的实验研究

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摘要

Impingement cooling through jet holes is a very attractive cooling system for heat rejection at high heat loaded areas as the leading edge of turbine vanes. Although some correlations and tools are available to dimension such systems, the variety and complexity of the flow features present in those systems still require experimental validation of real engine designs. Among the experimental techniques possible to be used, transient liquid crystal method offers good resolution as well as sufficient accuracy. Under this investigation, an impingement cooling system for the leading edge of a contrarotating power turbine (PT) representative of a small turboshaft engine was investigated experimentally. The PT vane features a very thin leading edge with high curvature and side channels rapidly turning backward. Constraints on cooling flow consumption and distribution led to a leading edge configuration with two rows of staggered jets. This particular configuration was experimentally investigated for three different Reynolds numbers around the design point by using a transient liquid crystal technique, which allows the measurement of surface distribution of heat transfer coefficient at the area of interest. Heat transfer results are presented in terms of surface distributions, impingement rows stagnation line local distributions, streamwise distributions along planes over the impingement stagnation points, span averaged streamwise local distributions, and surface averaged values. These results are then compared with available correlations from existing literature showing good matching for both maximum and averaged values. The results are also used as baseline data to discuss some of the flow features that can have effect on the heat transfer on this particular configuration.
机译：通过喷射孔进行冲击冷却是一种非常吸引人的冷却系统，用于在高热负荷区域（作为涡轮机叶片的前缘）排热。尽管可以使用一些相关性和工具来确定此类系统的尺寸，但这些系统中存在的流动特征的多样性和复杂性仍然需要对实际发动机设计进行实验验证。在可能使用的实验技术中，瞬态液晶法提供了良好的分辨率和足够的精度。在这项研究中，对代表小型涡轮轴发动机的反向旋转动力涡轮（PT）的前缘的冲击冷却系统进行了实验研究。 PT叶片的前缘非常薄，具有很高的曲率，并且侧面通道快速向后转动。冷却流消耗和分配的限制导致了具有两排交错射流的前沿配置。通过使用瞬态液晶技术，针对设计点周围的三个不同雷诺数，对这种特殊的配置进行了实验研究，该技术可以测量感兴趣区域的传热系数的表面分布。根据表面分布，冲击行停滞线局部分布，冲击停滞点沿平面的流向分布，跨度平均流向局部分布以及表面平均值来表示传热结果。然后将这些结果与现有文献中显示出的最大值和平均值均具有良好匹配性的相关性进行比较。结果也用作基线数据，以讨论可能对这种特定配置的传热产生影响的某些流动特征。

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