尾迹对低压涡轮吸力面附面层流动的影响  

Influence of the Wakes on the Suction Surface Boundary Layer of Low Pressure Turbine

作　　者：曹惠玲[1] 吴兴爽 谭天荣[1] 宋立旗 刘福林 CAO Hui-ling;WU Xing-shuang;TAN Tian-rong;SONG Li-qi;LIU Fu-lin(School of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《航空发动机》2022年第5期65-72,共8页Aeroengine

基　　金：天津市研究生科研创新项目(2019YJSS074)资助。

摘　　要：为研究尾迹对低压涡轮叶片吸力面附面层流动特性与转捩过程的影响,利用商用CFX软件进行数值模拟,并辅以试验校核。着眼于附面层瞬态分析,在1个尾迹扫掠周期内,对吸力面附面层内Klebanoff条纹、KH结构、涡等瞬态结构进行研究。结果表明:在尾迹间歇期,尾迹诱导湍流区和抑制区仍在影响叶片尾缘附面层的发展,分离泡在抑制区上游重新生成;尾迹接触叶片前缘后,产生尾迹放大Klebanoff条纹,其前缘以88%的主流速度向下游运动,随后尾迹接触附面层并与分离泡作用,触发剪切层的KH不稳定性形成全展向KH卷起涡,而尾迹诱导转捩起到了抑制分离泡的作用;尾迹放大Klebanoff条纹将追赶并冲击全展向KH卷起涡,使其崩溃为局部KH涡并最终破裂成全湍流。In order to study the influence of wake on the flow characteristics of suction surface boundary layer and transition process of low pressure turbine blade,commercial CFX software was used for numerical simulation,and test verification was carried out.Focusing on the transient analysis of the boundary layer,the Klebanoff streaks,KH structure,vortices and other transient structures in the suction surface boundary layer were studied in one wake-passing cycle.The results show that the wake-induced turbulence zone and the calmed zone still affect the development of the blade trailing edge boundary layer during the wake intermittent period,and the separation bubbles regenerate upstream of the calmed zone.After the wake contacts the blade leading edge,the amplified Klebanoff streaks of the wake is generated,and the leading edge moves downward at 88%of the mainstream speed.Then the wake contacts the boundary layer and interacts with the separation bubble,triggering the KH instability of the shear layer to form a full-span KH rolling vortex,and the wake induced transition plays a role in suppressing the separation bubble.The Klebanoff streak with enlarged wakes will catch up and impinge on the full-span KH vortex,causing it to collapse into a local KH vortex and eventually rupture to form turbulence.

关 键 词：尾迹 低压涡轮叶片 附面层 尾迹诱导转捩 自然转捩 瞬态结构 航空发动机 

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]