针对压气机叶栅角区流动易分离的特点,提出一种在叶栅前缘安装小叶片来抑制角区分离的新型流动控制方法。在利用叶栅试验数据确认数值模拟的可靠性后,对不同攻角下安装小叶片前后叶栅的流场特性进行了数值研究。结果表明:在-6°到9°攻角范围内小叶片改善了扩压叶栅的气动性能,使得总压损失减小,静压升增大。小叶片能使叶栅角区前缘分离点后移,角区分离线后的反流区面积减小,改善了角区流动;更多的流体汇聚到中间叶高,增强叶中部载荷,提高了叶栅的扩压能力。 Aiming at the characteristics of easy flow separation in the compressor cascade at the corner, a new flow control method was proposed, in which the small blades were installed on the leading edge of the cascade to restrain the angular separation. After confirming the reliability of the numerical simulation by using the cascade test data, the numerical simulation of the flow field before and after the installation of small vanes under different angles of attack was carried out. The results show that the small blade improves the aerodynamic performance of the diffuser cascade in the range of -6 ° to 9 ° angle of attack, resulting in a decrease of total pressure loss and an increase of static pressure. Small blades can make the separation point of the leading edge of the cascade move backward and the area of ​​the backflow zone decreases after the separation of the corner and improve the flow in the corner. More fluid converges to the middle of the leaf and enhances the middle leaf load, Cascade diffuser capacity.