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使用NUMECA软件对某型超音速两级冲击式涡轮进行了全三维定常湍流流场计算,分析了计算结果。以此为基础,通过修改叶型得到性能较高的涡轮叶型设计,并对比了优化前后涡轮内部流场。以三维计算结果为基础,分析涡轮内部流动损失,在保证氧涡轮原有机械结构不做大的改变、输入条件不变的情况下,对涡轮叶型进行优化研究。以叶型参数为变量,以总静效率(在总总效率的基础上考虑余速损失而得)为目标函数,通过反复修改各个叶型参数,然后对每次修改过的叶片进行三维计算,通过比较涡轮总静效率大小判断叶型优劣。通过优化,获得了效率更高、做功能力更强的涡轮叶型。研究成果对工程研制有一定的指导意义,总结的涡轮气动设计及优化方法,对涡轮的设计具有借鉴作用。
The NUMECA software is used to calculate the full three-dimensional turbulent flow field of a supersonic two-stage impact turbine, and the calculation results are analyzed. Based on this, the turbine blade design with higher performance is obtained by modifying the blade shape, and the flow field inside the turbine before and after optimization is compared. Based on the three-dimensional calculation results, the flow loss inside the turbine was analyzed. The turbine blade type was optimized under the condition of keeping the original mechanical structure of the oxygen turbine unchanged and the input condition unchanged. Taking the leaf type parameter as the variable, taking the total static efficiency (taking into account the residual loss on the basis of the total efficiency) as the objective function, by repeatedly modifying each leaf type parameter, and then performing three-dimensional calculation on each modified leaf, By comparing the total efficiency of the turbine to determine the overall efficiency of the leaf type. Through optimization, the turbine blades with higher efficiency and stronger work ability are obtained. The research results have certain guiding significance for engineering development. The summary of the turbo aerodynamic design and optimization methods can be used as a reference for the design of the turbine.