中文摘要：

针对跨音速压气机通道内部由于激波以及叶片角区内低能流体聚集产生附面层分离导致的流动失稳问题,本文基于叶列间流动匹配与控制叶型中弧线曲率的优化设计思想,以E~3高压压气机的前1.5级为蓝本,在级环境下对其转子叶片开展气动优化设计研究。研究结果表明,基于叶型中弧线曲率控制技术的叶片气动优化设计技术能够有效减少优化变量的数目,有效地改善压气机叶片设计点与非设计点的气动性能。

英文摘要：

On the flow instability caused by the boundary-layer flow separation due to the shock wave and the low-energy fluid accumulation in the corner area for the transonic compressor passage,based on the optimization design concepts of matching flow between blade rows and control the camber line curvature,a rotor blade is optimized for a 1.5-stage compressor in the E3.The results indicates that the aerodynamic optimization design technique based on the curvature control method for camber line can skillfully reduce the number of optimization variables and effectively improve the aerodynamic performance of the compressor blade passage at design and off-design points.