Numerical study of film cooling at the outlet of gas turbine exhaust

Longbing Hu, Yu Rao, Hua Zhang
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Abstract

In order to mitigate the potential operational damage risk caused by traditional cooling methods in engineering applications of heavy-duty gas turbine component testing, the film cooling unit and realizable K-epsilon turbulence model were employed. Numerical simulations were conducted for multiple exhaust film holes with varying curvature and pitch-row under different operating conditions. The heat transfer distribution along the flow direction and radial direction of the high temperature wall was analyzed, as well as the influence of heat transfer under different geometrical parameters. The results indicate that for the integrated configuration of large-diameter cooling units, a blowing ratio of 0.3 yields the most comprehensive cooling effect, primarily due to the extensive spatial coverage by the gas film and the weakening of eddy dissipation mechanisms. Additionally, it was observed that with an increase in hole distance ratio for multiple exhaust film holes, cold air could more stably participate in heat exchange with high-temperature flue gas wake at the outlet of the gas film hole; thus, a hole distance ratio of 3.0 provides optimal comprehensive cooling effects.
燃气轮机排气口薄膜冷却的数值研究
为了降低重型燃气轮机部件测试工程应用中传统冷却方法造成的潜在运行损坏风险,采用了薄膜冷却装置和可实现的 K-epsilon 湍流模型。在不同的运行条件下,对具有不同曲率和间距的多个排气膜孔进行了数值模拟。分析了沿流向和高温壁径向的传热分布,以及不同几何参数对传热的影响。结果表明,对于大直径冷却单元的集成配置,0.3 的吹气比产生的冷却效果最全面,这主要是由于气膜的广泛空间覆盖和涡流耗散机制的减弱。此外,还观察到随着多个排气膜孔的孔距比增加,冷空气可以更稳定地参与气膜孔出口处高温烟气唤醒的热交换;因此,3.0 的孔距比可以提供最佳的综合冷却效果。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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