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为解决涡轮静叶尾缘烧蚀问题并提升气动效率,采用气热耦合优化的方法对该叶片进行优化,优化分为对叶型优化以及对弯叶片优化两部分。优化结果显示,对叶型进行优化时由于叶型变化以及冷气流量增加2.68%导致叶片平均温度降低4.15%,最高温度下降61.7K,气动效率提升0.17%;对弯叶片进行优化时,顶部正弯效果明显,冷气流量增加0.11%,叶片平均温度下降2.4%,最高温度下降10.6K,气动效率提升0.16%。通过分析,对于该径高比较小的叶片,无论是叶型变化还是弯叶片变化,低能流体由端区进入主流导致的端区损失降低和激波损失的降低是导致气动效率提升的主要原因;冷气流量加大以及端区二次流减弱是造成叶片温度场降低的主要原因。
In order to solve the problem of the ablation of the turbine vane trailing edge and improve the aerodynamic efficiency, the aerodynamic optimization was used to optimize the vane. The optimization was divided into optimization of vane and optimization of vane. The optimization results show that the leaf temperature is reduced by 4.68%, the maximum temperature is decreased by 61.7K and the aerodynamic efficiency is increased by 0.17% due to the changes of the leaf shape and the increase of air flow rate by 2.68% The effect is obvious, air flow increased by 0.11%, leaf average temperature decreased by 2.4%, the maximum temperature dropped 10.6K, aerodynamic efficiency increased 0.16%. Through analysis, it is the main reason that the efficiency of aerodynamic efficiency is increased because of the decrease of tip area and the loss of shock caused by the low-energy fluid entering the mainstream from the end zone, The increase of cold air flow and the decrease of the secondary flow in the end zone are the main reasons for the decrease of the temperature field of the blade.