为了研究来流边界层对跨声速压气机转子气动性能及流场的影响，针对Rotor37进行了不同来流边界层进口条件下的跨声速压气机流场数值模拟。结果表明：来流边界层引起其内部的激波结构变化，进而影响60%叶高以上流场，造成该展向范围内的流量分布发生再分配；在来流边界层具有相同的厚度时，总压亏损越大，以60%~90%叶高激波损失为主体的附加损失越高；来流边界层弱化了叶尖泄漏涡系的强度，通过同时改变叶尖负荷和叶尖泄漏流来源流体能量影响泄漏强度，进而影响泄漏涡系的形成和发展。

In order to investigate the influence of incoming boundary layer on the aerodynamic performance and flow field of transonic compressor rotor,the numerical simulation of the transonic compressor flow field with different incoming boundary layer was inlet conditions carried out for rotor 37.The results show that the incoming boundary layer causes the change of shock wave structure inside the boundary layer,and then affects the flow field above 60% span,resulting in the redistribution of the mass flow in the spanwise.When incoming boundary layer thickness is the same,the greater the total pressure deficit is,the higher the additional loss with 60% to 90% span shock loss as the main body is.The incoming boundary layer weakens the strength of tip leakage vortex system,which influences the leakage strength by simultaneously changing tip load and tip leakage flow source fluid energy,and thus affects the formation and development of the leakage vortex system.

V231.3

国家科技重大专项（2017-I-0011-0012）