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首页> 外文期刊>International Journal of Heat and Mass Transfer >Numerical simulation on the effect of jet nozzle position on impingement cooling of gas turbine blade leading edge
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Numerical simulation on the effect of jet nozzle position on impingement cooling of gas turbine blade leading edge

机译：喷嘴位置对燃气轮机叶片前缘冲击冷却影响的数值模拟

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摘要

In this paper, Computational Fluid Dynamics (CFD) simulations are performed to investigate the impingement cooling on internal leading edge region which is stretched by the middle cross section of the first stage rotor blade of CE-E3 engine high pressure gas turbine. The simulations are carried out for a blade with a single row of circle jets at five different positions and seven different inlet flow Mach numbers. The results indicate that the global area weighted average Nusselt number at the blade leading edge increases with the increase of jet Mach number, and increases with the decrease of the distance between the jet nozzle and the pressure side. The correlation for the area weighted average Nusselt number as a function of the parameters is derived for the range of the parameters considered. The streamwise length weighted average Nusselt number and the spanwise length weighted average Nusselt number also increase with the decrease of the spacing between the jet nozzle and the pressure side, and increase with the increase of jet Mach number. The side entry jet is desirable to improve the performance of impingement cooling on turbine leading edge, but the arrangement of the jet nozzle and the shape of the internal cooling passage should be further optimized to improve the distribution of the heat transfer coefficient.
机译：本文通过计算流体动力学（CFD）仿真研究了CE-E3发动机高压燃气轮机的第一级动叶片中间截面所拉伸的内部前缘区域的冲击冷却。对在五个不同位置和七个不同入口流量马赫数的单排圆形喷嘴的叶片进行了仿真。结果表明，叶片前缘的总面积加权平均努塞尔数随射流马赫数的增加而增加，随射流喷嘴与压力侧之间距离的减小而增加。对于所考虑的参数范围，得出面积加权平均努塞尔数随参数的相关性。流向长度加权平均努塞尔数和跨径长度加权平均努塞尔数也随着喷嘴与压力侧之间的间距的减小而增加，并且随着射流马赫数的增加而增大。侧面入口射流是期望的，以改善涡轮机前缘上的冲击冷却性能，但是应该进一步优化射流喷嘴的布置和内部冷却通道的形状，以改善传热系数的分布。

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