不同静叶间隙对近失速条件下压气机流场的影响

采用数值模拟方法，研究不同弦向长度的间隙结构对近失速工况下跨声速压气机静叶流场结构以及气动性能的影响，探究叶顶间隙泄漏流对角区分离的影响机理.研究结果表明：静叶顶部间隙产生的泄漏流可吹除角区的低能流体团，抑制吸力面侧的角区分离，削弱流道堵塞情况，有效推迟了压气机失速；静叶前部间隙对叶栅性能的改善情况与全间隙类似，而后部间隙对压气机的性能影响较小，且降低了压气机的稳定裕度.
Numerical simulation was used to study the effects of different chord length clearance structures on the flow field structure and aerodynamic performance of the transonic compressor stator blade under near stall condition, and the influence mechanism of tip clearance leakage flow on corner separation was also studied. Results show that the leakage flow produced by the tip clearance can eliminate the low energy fluid in the corner region, weaken the separation of the suction side, and reduce the blockage of convection, which delay the compressor stall. The front clearance improves the stator cascade performance as well as the full clearance. However, the rear clearance has little effect on the compressor performance, and the stability margin of the compressor is reduced.