基于马蹄涡前缘吸气控制的压气机叶栅流动机理  

Flow mechanism of horseshoe vortex suction control for compressor cascade

作　　者：唐耀璇 刘艳明[1] 安宇飞 孙运政 TANG Yaoxuan;LIU Yanming;AN Yufei;SUN Yunzheng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《北京航空航天大学学报》2024年第4期1282-1291,共10页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为探究从源头抑制角区分离的流动控制方法,采用数值模拟方法,以NACA65叶栅为研究对象,利用叶栅前缘端壁吸气技术控制马蹄涡,结合拓扑分析对叶栅通道内的三维流动结构进行精确重构,以研究前缘端壁吸气控制马蹄涡进而改善叶栅通道流场结构的机理。结果表明:叶栅前缘端壁吸气技术可以有效推迟马蹄涡形成并削弱其强度,同时在吸气狭缝末端形成一对反旋流向涡对,在向下游发展过程中与通道涡相互作用;前缘端壁吸气通过控制马蹄涡,降低端壁边界层厚度,叶栅前缘通道涡发展受限,由回流组成的叶表分离被抑制;前缘及压力面侧吸气(EPS)直接作用于马蹄涡压力面分支,通道涡强度进一步被削弱,角区分离模式由闭式分离转为不完全闭式分离。最后,对比最优吸气系数下不同方案出口总压损失,发现当吸气量为进口质量流量的0.2%时,EPS方案出口截面总压损失降低5.8%;并且通过调整吸气系数,可以获得较好的变工况控制性能。To explore the source flow control method for the corner separation,this paper takes the NACA65 cascade as the research object and applies the blade leading edge endwall suction technology to control the horseshoe vortex with the numerical simulation method.Combined with topology analysis,the three-dimensional flow field is accurately reconstructed and the control mechanism of the leading edge endwall suction is revealed to improve the cascade channel flow field performance.The results show that the leading edge endwall suction technology can effectively delay the formation of the horseshoe vortex and weaken its strength.Meanwhile,a pair of counter rotating vortices are formed at the end of the suction slit,which interacts with the passage vortex in the process of downstream development.By regulating horseshoe vortices,the suction lessens the thickness of the endwall boundary layer,inhibiting the formation of leading edge passage vortices and preventing surface separation caused by backflow.Because the leading edge and pressure side suction(EPS)directly acts on the pressure side leg of the horseshoe vortex,the passage vortex strength is further weakened,and the corner separation mode changes from closed separation to incomplete closed separation.Finally,the total pressure losses are compared at the outlet under the optimal suction coefficient.It is discovered that when the suction coefficient is 0.2%,the overall pressure loss at the EPS outflow section is decreased by 5.8%.At off-design situations,improved control performance can be attained by modifying the suction coefficient.

关 键 词：压气机叶栅 马蹄涡 角区分离 前缘吸气 拓扑分析 

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] TB553[理学—物理]