Numerical study on the effect of jet nozzle aspect ratio and jet angle on swirl cooling in a model of a turbine blade leading edge cooling passage
Numerical study on the effect of jet nozzle aspect ratio and jet angle on swirl cooling in a model of a turbine blade leading edge cooling passage
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DOI：
10.1016/j.ijheatmasstransfer.2015.07.050
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发表时间：
2015-11
影响因子：
5.2
通讯作者：
Zhaofang Liu;Jun Li;Z. Feng;T. Simon
中科院分区：
文献类型：
--
作者：
Zhaofang Liu;Jun Li;Z. Feng;T. Simon
在本文中，进行数值模拟来预测燃气轮机叶片内部前缘冷却通道模型的涡流冷却。针对两个矩形截面入口导致流体切向冲击圆形冷却通道内表面的情况，研究了旋流冷却性能及其有效性。研究了喷嘴长宽比、喷射角度和雷诺数对局部和平均流动以及传热的影响。结果表明，旋流室压力损失和全局面积加权平均努塞尔数随着雷诺数的增大而增大，随着喷嘴长径比的减小而增大。建议在一系列参数上建立面积加权平均努塞尔数的相关性。旋流室内的努塞尔数分布表明，喷嘴角度为 60° 时热应力最低。
In this paper, a numerical simulation is performed to predict swirl cooling of an internal leading edge cooling passage model for a gas turbine blade. The swirling cooling performance and its effectiveness are investigated for cases of two rectangular section inlets that cause flow to impinge tangentially on the internal surface of the circular cooling passage. The effects of aspect ratio of the jet nozzle, jet angle and Reynolds numbers on the local and average flows and heat transfer are investigated. The results indicate that the pressure loss and global area weighted average Nusselt number on the swirl chamber increases with increases of Reynolds number, and increases with decreases of the jet nozzle aspect ratio. A correlation of the area weighted average Nusselt number over a range of parameters is suggested. The distribution of Nusselt number over the swirl chamber shows that the thermal stresses will be lowest with a 60° jet nozzle angle.