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Optimization of Turbine Blade Cooling Using Combined Cooling Techniques

机译：联合冷却技术优化涡轮叶片冷却

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AbstractThis paper presents analysis and optimization of turbine bade cooling systems. Since the temperature of combustion gases is very high sometimes reaching 2400 K, the turbine blade cannot sustain the resulting thermal stress. Moreover, for higher efficiency for advanced gas turbines, increase of inlet temperature is needed. Common blade cooling methods are film cooling, convection cooling, impingement cooling and combined cooling. In this paper, a numerical solution of the thermal and flow fields in film cooling technique on the AGTB expand symmetrical turbine blade was obtained and the results were validated with experimental data. Then the turbine blade geometry was changed and two combined cooling (impingement/convection cooing and impingement/film cooling) techniques were evaluated. The low Reynolds number k-ε turbulence model (AKN) was used for the turbulent flow simulations at various blowing ratios for two blade thicknesses. Comparisons of the results between the available experimental and nu...
机译：摘要本文介绍了汽轮机冷却系统的分析和优化。由于燃烧气体的温度很高，有时会达到2400 K，因此涡轮叶片无法承受由此产生的热应力。此外，为了提高先进燃气轮机的效率，需要增加入口温度。常见的叶片冷却方法是薄膜冷却，对流冷却，冲击冷却和组合冷却。本文对AGTB膨胀对称透平叶片的薄膜冷却技术中的热流场和流场进行了数值求解，并用实验数据验证了结果。然后，改变涡轮叶片的几何形状，并评估两种组合的冷却（冲击/对流冷却和冲击/薄膜冷却）技术。低雷诺数k-ε湍流模型（AKN）用于在两种叶片厚度下以不同吹风比进行的湍流模拟。可用的实验结果和新的结果之间的比较

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