关键词: 流动控制;压气机叶栅;扫频式射流;角区分离

Abstract: Large scale separation is responsible for the performance deterioration of highly-loaded compressors. Numerical method was employed to study the effect of the sweeping jet to manage the corner separation and reduce aerodynamic losses. The actual sweeping jet actuator was replaced with governing equations to provide further discussions of the influence of several governing parameters on the aerodynamic performance enhancement and flow field improvements. The results supported the following conclusions. Firstly, a steady periodic variation existed under the flow field with sweeping jets. A governing excitation frequency could be found that with excitation frequencies larger than the governing excitation frequency, the total pressure loss reduction in the compressor cascade with sweeping jets turned out to be similar. Besides, appropriate excitation parameter arrangements were crucial to the control of separation. The sweeping jets with a smaller excitation jet angle to the suction surface and a smaller excitation jet velocity obtained better flow control performance against the corner separation. The effectiveness of the flow control was enhanced with larger sweeping angle with a 6.1% reduction of total pressure loss at most. Finally, the aerodynamic improvements mechanism with sweeping jet were pointed out to be larger excited region of low momentum fluids in the suction side boundary layer and stronger restriction of the development of the corner separation toward blade spanwise.