The aim of this article mainly lies in two aspects. The first is to investigate the effect of inlet swirl distortion on the performance and stability of a low-speed compressor experimentally. The second is to quantify swirl pattern revolution through the compressor and find out background causes of the change in compressor performance. Swirl distortion makes the leading-edge incidence opposite between tip and hub regions, compared to that of clean flow. And the compressor performance change is ultimately determined by these two aspects. Results indicate that negative bulk swirl improves pressure rise, and the effect is on the contrary to the positive bulk swirl. Under the condition of paired swirl, pressure rise also presents a reduction. All these three types of swirl have little effect on the stall boundary. Although swirl distortion shows clear recovery at rotor exit, downstream components still work at off-design conditions due to the induced nonuniformity in axial velocity and total pressure.

本文的目的主要在于两个方面。首先是通过实验研究入口涡流畸变对低速压缩机性能和稳定性的影响。第二个是量化压缩机的涡流模式旋转，并找出压缩机性能变化的背景原因。与清洁流相比，旋流畸变使得尖端区域和轮毂区域之间的前缘入射方向相反。而压缩机性能的变化最终是由这两方面决定的。结果表明，负整体涡流改善了压力上升，且效果与正整体涡流相反。在成对旋流条件下，压力升高也呈现降低趋势。所有这三种类型的涡流对失速边界影响很小。尽管涡流畸变在转子出口处显示出明显的恢复，但由于轴向速度和总压力的不均匀性，下游部件仍然在非设计条件下工作。