改进的反问题边界条件在叶轮机械中的应用

Application of Improved Inverse Method Boundary Condition in Turbomachinery

为减小气流分离对叶轮机械反问题计算的影响,本文以三维黏性反问题设计方法理论为基础,对反问题所采用的边界条件进行了改进。文中以美国国家航空航天局Rotor 67跨声速转子为算例,进行叶片返回实验,以研究方法的正确性与可靠性,并将该计算结果与采用原始发问题边界条件的计算结果进行对比。结果表明,相比原反问题边界条件,改进的反问题边界条件的反问题计算受气流分离影响较小,计算结果满足了给定的气动参数分布,叶片几何与目标几何吻合较好。

In order to reduce the influence of flow separation on turbomachinery inverse method,an improvement of inverse method boundary condition is made based on the three dimensional viscous inverse design method theories.The NASA Rotor 67 transonic rotor experiment data is used to validate the method.Then,the calculation result is compared with original inverse method boundary condition.The numerical research shows improved inverse method boundary condition is less affected by the flow separation,and better accuracy is achieved in terms of aerodynamic parameters distribution and blade geometry recovery.