高负荷低压涡轮时序效应数值模拟与试验验证  

Numerical Simulation and Experimental Verification of Clocking Effect of High-lift Low Pressure Turbine

作　　者：杨晓军[1] 宋立旗 宁嘉昕 康晋辉 YANG Xiao-jun;SONG Li-qi;NING Jia-xin;KANG Jin-hui(School of Aeronautical 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》2023年第5期121-128,共8页Aeroengine

基　　金：天津市研究生科研创新项目(2019YJSS074)资助。

摘　　要：为了研究上下游叶片的相位对低压涡轮流动的影响机理,使用商用CFX软件进行数值模拟,并辅以试验校核。选取了0°和180°2个流动相差较大的相位,分析边界层分离与转捩、边界层积分参数,对吸力面的载荷系数、壁面剪力、附面层形状因子及动量厚度等进行对比,并从边界层的瞬态流动分析着手,在1个尾迹扫掠周期内对Klebanoff条纹、K-H涡等结构进行分析。结果表明:不同相位的流动特性差异主要取决于势流的压力扰动与速度扰动的相位,这将决定尾迹诱导转捩与寂静区之间的主导关系。当压力扰动与速度扰动同相时,寂静区处于逆压梯度逐渐增强的阶段,保持层流的能力被削弱;反之当二者异相时寂静区强度较大,尾迹诱导转捩带来的湍流损失可以被寂静区平衡。通过瞬态分析可知,0°相位尾迹诱导全展向K-H涡的卷起,全展向涡的破碎会带来较大的能量耗散,且其诱导的Klebanoff条纹强度较大,二者共同作用使得尾缘动量损失较大。In order to study the influence mechanism of clocking of upstream and downstream blades on low-pressure turbine flows,numerical simulation was conducted using commercial CFX software,and supplemented by experimental verification.Two highly distinct phasesφ=0°andφ=180°were chosen for the study,analyses were conducted by investigating boundary layer separation and transition and boundary layer integral parameters,comparing load coefficient,wall shear stress,boundary layer shape factor and momentum thickness,and by analyzing the transient flow of the boundary layer,Klebanoff streaks,and K-H vortices.The results show that the difference in flow characteristics with different phases mainly depends on the phase of potential flow pressure disturbance and velocity disturbance,which determines the dominant relationship between wake induced transition and the calmed region.When the disturbance of pressure and velocity are in-phase,the potential to maintain laminar flow of calmed region is weakened because of the increasing adverse pressure gradient.On the contrary,when the two are out-of-phase,the calmed region is elevated,balancing the turbulence loss caused by wake induced transition.Instantaneous analysis shows that the wake induced full-span K-H vortices roll up atφ=0°,the break-down of full-span vortices produce great energy dissipation,and the Klebanoff streaks induced by the wake are of high intensity,which both lead to a large trailing edge momentum loss.

关 键 词：高负荷低压涡轮 时序效应 尾迹诱导转捩 寂静区 瞬态分析 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]