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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.4 pt.B; 20070514-17; Montreal(CA) >EXPERIMENTAL AND NUMERICAL IMPINGEMENT HEAT TRANSFER IN AN AIRFOIL LEADING-EDGE COOLING CHANNEL WITH CROSSFLOW
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EXPERIMENTAL AND NUMERICAL IMPINGEMENT HEAT TRANSFER IN AN AIRFOIL LEADING-EDGE COOLING CHANNEL WITH CROSSFLOW

机译：横流翼型前沿冷却通道的传热与数值模拟

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摘要

To enhance the internal heat transfer around the airfoil leading-edge area, a combination of rib-roughened cooling channels, film cooling and impingement cooling is often employed. Experimental data for impingement on various leading-edge geometries are reported by these and other investigators. Effects of strong crossflows on the leading-edge impingement heat transfer, however, have not been studied to that extent. This investigation dealt with impingement on the leading-edge of an airfoil in the presence of crossflows beyond the crossflow created by the upstream jets (spent air). Measurements of heat transfer coefficients on the airfoil nose area as well as the pressure and suction side areas are reported. The tests were run for a range of axial to jet mass flow rates (M_(axial)/M_(jet)) ranging from 1.14 to 6.4 and and jet Reynolds numbers ranging from 8000 to 48000. Comparisons are also made between the experimental results of impingement with and without the presence of crossflow and between representative numerical and measured heat transfer results. It was concluded that the presence of the external crossflow reduces the impinging jet effectiveness both on the nose and side walls, even for an axial to jet mass flow ratio as high as 5, the convective heat transfer coefficient produced by the axial channel flow was less than that of the impinging jet without the presence of the external crossflow, and the agreement between the numerical and experimental results was reasonable with an average difference ranging from -8% to -20%.
机译：为了增强机翼前缘区域周围的内部热传递，通常采用肋筋粗糙的冷却通道，薄膜冷却和冲击冷却的组合。这些研究人员和其他研究人员报告了撞击各种前沿几何形状的实验数据。但是，尚未研究到强横流对前沿碰撞传热的影响。这项研究处理了在存在上游气流（耗气）产生的交叉流之外的交叉流的情况下，对机翼前缘的冲击。报告了在翼型鼻部区域以及压力和吸力侧面区域的传热系数的测量结果。对轴向到射流的质量流量（M_（轴向）/ M_（射流））的范围从1.14到6.4进行了测试，并且射流雷诺数在8000到48000的范围内进行了测试。在有或没有横流的情况下以及在代表性数值和实测传热结果之间的碰撞。得出的结论是，外部错流的存在会降低鼻和侧壁上的撞击射流效率，即使轴向与射流的质量流量比高达5，轴向通道流产生的对流传热系数也较小与没有外部横流的撞击射流相比，数值和实验结果之间的一致性是合理的，平均差异为-8％至-20％。

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