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首页> 外文期刊>International Communications in Heat and Mass Transfer >Cooling methods for gas turbine blade leading edge: Comparative study on impingement cooling, vortex cooling and double vortex cooling
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Cooling methods for gas turbine blade leading edge: Comparative study on impingement cooling, vortex cooling and double vortex cooling

机译：燃气轮机叶片前缘的冷却方法：冲击冷却，涡流冷却和双涡流冷却的比较研究

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摘要

To compare the behavior of different cooling methods for gas turbine blade leading edge, configurations of impingement cooling, vortex cooling and double vortex cooling are established. The coolant chamber is specially introduced to make models closer to real leading edge cooling system. Numerical computation is performed based on the 3D viscous steady Reynolds Averaged Navier-Stokes (BANS) equations and the k-co turbulence model. Results show that the flow mass of nozzles in all configurations increases from upstream to downstream with the introduction of the coolant chamber. Besides, it is found that the anti-crossflow ability of nozzles is important to the flow and heat transfer performance. Lower crossflow velocity as well as smaller upwind nozzle area contributes to stronger anti-crossflow ability of nozzles. The vortex cooling proves to be a good cooling method with the highest heat transfer intensity and thermal performance factor, but its pressure loss is much larger. The middle-double vortex cooling is actually the optimization of the impingement cooling configuration and it has the lowest pressure loss. The tangential-double vortex cooling isn't applicable to leading edge cooling due to poor flow and heat transfer performance.
机译：为了比较不同冷却方法对燃气轮机叶片前缘的性能，建立了冲击冷却，涡流冷却和双涡流冷却的配置。专门引入了冷却剂室，以使模型更接近真实的前沿冷却系统。基于3D粘性稳态雷诺平均Navier-Stokes（BANS）方程和k-co湍流模型进行数值计算。结果表明，随着冷却剂腔的引入，所有配置的喷嘴流量都从上游到下游增加。此外，发现喷嘴的抗错流能力对于流动和传热性能很重要。较低的横流速度以及较小的迎风喷嘴面积有助于增强喷嘴的抗横流能力。涡流冷却被证明是一种具有最高传热强度和热性能因子的良好冷却方法，但是其压力损失要大得多。中双涡旋冷却实际上是对冲击冷却配置的优化，并且压力损失最低。由于流量和传热性能较差，切向双涡旋冷却不适用于前沿冷却。

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