附面层抽吸技术在跨声速平面叶栅试验中的应用探索  

Application of boundary layer suction technology on the transonic cascade experiments

作　　者：向宏辉[1,2] 侯敏杰[2] 梁俊[2] 葛宁[1] 刘志刚[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703

出　　处：《燃气涡轮试验与研究》2015年第1期1-6,共6页Gas Turbine Experiment and Research

摘　　要：基于常规跨声速扩压叶栅吹风试验结果确定合理抽吸位置,并在此基础上对该叶栅进行多种工况的附面层抽吸试验,分析附面层抽吸作用下叶片表面马赫数、出口尾迹与总压损失系数的变化。结果表明:开设抽吸缝对常规跨声速叶栅原有流场结构的总体影响较小,但当抽吸缝位于马赫数峰值位置时,会对下游流动产生一定扰动。在适当位置抽吸能抑制跨声速叶栅表面流动分离,且只有抽吸量达到一定数值后,附面层抽吸作用才会对叶栅气动性能起到明显正效果。当抽吸量达到0.87%时,该跨声速叶栅总压损失系数降低了7.8%。The reasonable suction position was determined according to conventional transonic diffuser cas？cade experimental results. The boundary layer suction experiments of the cascade were carried out under different operating conditions. The changes of blade surface Mach number distribution, outlet wake and to？tal pressure loss coefficient which caused by boundary layer suction effect were analyzed. The results indi？cated that the impact of slotting on the original flow field structure of conventional cascade was small. But when the suction slot was located in the peak Mach number position, it would produce effects on the down？stream flow of the cascade. The suction in proper position can suppress surface flow separation of the tran？sonic cascade, and only the suction flow rate reached a certain value, the boundary layer suction had signifi？cant positive effects on the cascade aerodynamic performance. The total pressure loss coefficient of the tran？sonic cascade decreased 7.8%when the suction flow rate was 0.87%.

关 键 词：航空发动机 跨声速叶栅 附面层抽吸 流动分离 总压损失系数 抽吸量 抽吸位置 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]