Shock Tube Experiment and Numerical Simulation on Transient Stall Characteristics and Active Stall Control in an Axial Flow Compressor

采用将激波管直接串联到压气机出口的轴流压气机试验台，对压气机在压气机下游压缩平面波注入下的非定常叶栅流动特性和压气机系统的整体性能进行了实验研究。随着压缩波的注入，动叶发生了短暂的失速，并由于工作点的差异呈现出复杂的非定常恢复过程。即使在特性曲线梯度为负的压气机稳定运行时注入压缩波，压气机系统也可能冲进旋转失速、喘振等非定常现象。此外，一些失速单元在转子叶栅内按较大的喘振周期旋转，发现旋转失速与喘振之间存在着密切的关系。

Experimental investigation on the unsteady cascade flow characteristics as well as global behavior of the compressor system under the compression plane wave injection from the compressor downstream were carried out by using an axial flow compressor test rig which connected the shock tube directly in series to its outlet. Rotor blades rushes into stall transitionally with the injection of a compression wave, and shows a complicated unsteady recovery process by the difference in an operating point. Even when the compression wave is injected at the time of compressor stable operation in which the gradient of the characteristic curve is negative, the compressor system may rush into unsteady phenomena such as rotating stall and surge. Moreover, some of the stall cells rotate within the rotor cascade according to a large-scale surge cycle, the rotating stall and surge are found to be related closely each other.