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为降低跨声速压气机叶片通道中的激波损失,提升跨声速压气机的气动性能,以三维粘性反问题设计方法理论为基础,发展了三维反问题设计方法,并对反问题所使用的边界条件进行了改进。在保持叶片总切向载荷不变的同时,通过调整叶片表面沿轴向的载荷分布,达到降低叶片通道内部的激波强度,减少激波损失的目的。为验证方法的正确性,文中运用NASA Rotor 67跨声速压气机转子实验数据与计算结果进行对比,在此基础上对叶片表面载荷进行分析,在修改叶片表面载荷分布后通过反问题设计方法得到新的叶片几何。结果表明,通过修改叶片表面载荷分布,运用反问题设计方法得到的新叶片,其激波强度明显降低,压气机转子出口流量提高了0.5%,效率提高了1.0%。
In order to reduce the shock loss in the transonic compressor blade passage and improve the aerodynamic performance of the transonic compressor, a three-dimensional inverse problem design method is developed based on the three-dimensional viscous reaction problem design method and the boundary Conditions have been improved. While keeping the total tangential load of the blade constant, the load distribution along the axial direction of the blade surface is adjusted to reduce the shock wave intensity inside the blade passage and reduce the shock loss. In order to validate the correctness of the method, the experimental data of the transonic compressor rotor of NASA Rotor 67 are compared with the calculated results. Based on this, the surface load on the blade is analyzed. After the modification of the load distribution on the blade surface, the new problem is obtained by the inverse problem design method Leaf geometry. The results show that the shock strength of the new blade obtained by the inverse problem design method is significantly reduced by modifying the blade surface load distribution. The flow rate at the exit of the compressor rotor is increased by 0.5% and the efficiency is improved by 1.0%.