脉冲型流体振荡器射流对叶栅角区分离的控制研究

Based on the unsteady numerical simulation method， the dual-hole oscillating jet was generated by the unique structure of the fluid oscillator， and its control mechanism to inhibit the compressor cascade corner separation at a high incidence angle was investigated. The effects of jet position， jet angle， jet flow rate， and single/array jet configurations on the control effect were carefully analyzed. The results indicate that for the single-jet configuration applied to the proximal endwall， the optimal jet position is located where the corner separation is not fully developed （54% blade axial chord length）. The optimal jet angle and jet flow ratio are determined to be 10° and 0.09%， respectively， resulting in a reduction of 6.48% in the total pressure loss coefficient and an increase of 2.39% in the static pressure rise coefficient. The oscillating jet effectively inhibits boundary layer development by injecting high flow momentum into the low-energy fluid within the boundary layer. Furthermore， the unsteady excitation of the oscillating jet breaks down the large-scale separation vortices on the suction surface into a series of small-scale vortices， and the frequency-locking effect reduces trailing edge pressure pulsation amplitude， ultimately leading to reduced loss. Compared to the single-jet configuration， the array-type jet configuration applies oscillating jet flow across the entire blade height， and the aerodynamic performance gain has doubled through inputting five times flow rate.