Abstract: Both boundary layer suction and shockwave exist in transonic low-reaction boundary layer suction compressor stator area. Thus the unsteady effect is strong and it is different from the general compressor. Unsteady numerical simulation was applied to the study of the transonic low-reaction boundary layer suction compressor. By comparative analysing two most representative moments，the impact of rotor-stator interaction on aerodynamic performance and flow field detail was explored. The results show that the flow is intense unsteady，the efficiency fluctuation achieves 0.937% in different moments. Rotor wake has a strong interaction with the domain before stator spanwise suction. In stator area，the separations mainly exist in three positions，that is 30% chord of suction side，top and bottom of suction side's trailing edge. Among the three separation，the reason causing the 30% chord of suction side separation is shockwave-boundary layer interference. In addition，the suction way of the low-energy fluid in that area is spiral path suction，also the positive and negative aspects of the spiral path suction to the flow field are analyzed in detail. The inner relationship among the shockwave-wake interference，shockwave-boundary layer interference and unsteady efficiency fluctuation is established. Finally，the root of the unsteady efficiency fluctuation is found out.

Key words: Transonic compressor；Low-reaction；Boundary layer suction；Rotor-stator interaction；Unsteady

摘要： 跨声速低反动度吸附式压气机的静叶流道中不但有附面层抽吸，还会存在由于低反动度设计而产生的激波，因而流动现象异于常规压气机，非定常效应明显，故采用非定常数值模拟方法，对跨声速低反动度吸附式压气机的内流场展开研究。通过选取两个最具代表性的时刻，探究了转静子干涉对该压气机气动性能以及内流场的影响。结果表明:非定常不同时刻的效率峰谷值之差达0.937%，流动的非定常性很强。转子尾迹对静子流道中展向抽吸缝前的区域干涉作用明显。在静叶流道中，分离主要存在于三个位置:30%弦长位置、尾缘顶部以及尾缘根部，其中静叶吸力面侧30%弦长位置的分离原因是激波与附面层干扰，且该处部分低能流体的吸除方式为“螺旋路径吸除”，并详细分析了其对流场的积极和消极影响。此外还建立了激波尾迹干涉——激波与附面层干扰——非定常效率波动这三者之间的联系，找出了非定常效率波动的原因。

关键词: 跨声速压气机；低反动度；附面层抽吸；转静子干涉；非定常