为给轴流压气机新型气动布局提供借鉴，进一步控制压气机角区分离，详细研究了静叶交替分布的静子对跨声速压气机气动性能的影响。以NASA Stage35单级轴流压气机为模型进行研究，基于控制角区分离的理论方法，调整静叶叶尖进口几何角，构造新型的交替静叶布局进行数值模拟并分析静叶改型压气机的气动特性。结果表明：不同的交替静叶模型对流动分离控制程度有较大差异，相比原型和全周静子叶片改型，交替静叶模型能够有效提升压气机性能，实现了压气机扩稳、增压以及等熵效率的提高。交替静叶模型的改型叶片叶尖进口几何角减小21°时，对压气机的性能提升效果最好，压气机的总压比和等熵效率均大幅提升且稳定裕度提升最大，相比原型提高了4.8%。

In order to provide a reference for the new aerodynamic configuration design of the axialflow compressor, and to further control the corner separation of the compressor, the effect of alternatingstator on the aerodynamic performance of a transonic compressor was detailly studied. Taking NASA stage35 singlestage axial compressor as the model, based on the theoretical method of control angle separation, the inlet geometric angle of the profile at stator tip was adjusted, and a new type of alternatingstator configuration was constructed for numerical simulation. The aerodynamic characteristics of the modified compressor was analyzed in detail. The results show that different alternatingstator models have different performances on controlling the corner separation. Compared with the original and the fullannulus modified compressor, the alternatingstator can effectively improve the compressor performance, and realize the enlargement of the stall margin and the improvement of the total pressure ratio and equal entropy efficiency of compressor. When the inlet geometric angle of the alternatingstator is reduced by 21°, the compressor has the largest performance improvement, the total pressure ratio and the isentropic efficiency of the compressor are greatly improved and the compressor has the largest improvement in stall margin. Compared with the original compressor, the stall margin is increased by 4.8%.