Rotor with tip squealer is often used in axial compressor of aircraft engine; however, its effect on the aerodynamic performance of axial compressor is not well understood. The purpose of this paper is to numerically investigate the effect of squealer on the performance of a 1.5-stage axial compressor. In comparison with flat tip, suction and pressure side squealers (SSS and PSS) with different height and thickness are implemented on the rotor blade of the compressor stage. Numerical result shows that pressure ratio is increased slightly under different working conditions with SSS. At the reference working point (RWP), SSS helps to increase mass flow while PSS reduces both mass flow and efficiency. Detailed analysis indicates that blade tip loading rises due to SSS while PSS introduces more losses in the tip region. When squealer is used, the amount of tip leakage flow stays almost unchanged, while vortex trajectory and distribution of leakage flow within tip gap are different. PSS enhances tip leakage flow near the leading edge, which makes the mixing of tip leakage flow and main flow faster and stronger.

带有尖齿的转子通常用于飞机发动机的轴向压缩机中。然而，它对轴向压缩机的空气动力性能的影响尚不十分清楚。本文的目的是通过数值研究尖叫器对1.5级轴向压缩机性能的影响。与平头相比，在压缩机级的转子叶片上安装了具有不同高度和厚度的吸气侧压力阀和压气侧压力阀（SSS和PSS）。数值结果表明，在不同工况下，SSS的压力比略有增加。在参考工作点（RWP），SSS帮助增加质量流量，而PSS降低质量流量和效率。详细的分析表明，由于SSS，叶片尖端载荷会增加，而PSS会在尖端区域引入更多的损耗。当使用尖叫声时，尖端泄漏流的数量几乎保持不变，而涡旋轨迹和尖端间隙内泄漏流的分布是不同的。PSS增强了前端附近的尖端泄漏流，这使尖端泄漏流与主流的混合更快，更强。