尾缘修型对探针支杆尾迹抑制作用的数值研究  

Numerical investigation on effects of reconstruction at probe support trailing edge on wake

作　　者：高杰 向宏辉[1,2] 杨荣菲[2] 王晖 葛宁[2] 

机构地区：[1]中国航发四川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 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2017年第1期28-31,35,共5页Gas Turbine Experiment and Research

基　　金：江苏省普通高校研究生科研创新计划项目(KYLX15_0260);四川省应用基础研究项目(2017JY0040)

摘　　要：为减小压气机试验中探针支杆尾迹对下游被测流场的干扰,以圆柱型探针支杆为研究对象,对其尾缘结构进行椭圆状修型处理,并采用数值模拟方法对支杆尾缘修型进行参数化研究,分析了修型几何参数对支杆尾迹旋涡抑制作用的变化规律。研究表明:支杆尾缘实施椭圆修型后所产生的总压损失随着椭圆长短半轴比值的增大而逐渐减小;当进口马赫数不大于0.50时,尾缘修型可推迟支杆表面附面层的流动分离,降低支杆尾迹掺混损失;当进口马赫数大于0.50时,尾缘修型虽能降低激波强度,但由于未能推迟壁面附面层分离,对尾迹损失抑制作用减弱。Aim to weaken the disturbance of probe support wake on measured flow field in compressor experiments, a cylinder probe support reconstructed according to ellipse shape at trailing edge, was investigated the effects of reconstruct geometric parameter on the wake vortex with numerical simulation method. The results show that the total pressure loss around reconstructed probe support decreases with the rise of ratio of long to short half axis. When the mach number at inlet is less than or equal to 0.5, support reconstructing at trailing edge could delay the boundary layer separation at wall surface and decrease its wake loss. But when the mach number is greater than 0.5, the reconstruction method could weaken shock intensity a little, however not decrease the flow loss greatly owing to that the boundary layer separation on wall surface is not delayed.

关 键 词：压气机试验 流场测量 探针支杆 尾缘修型 尾迹损失 总压损失 附面层分离 数值模拟 

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]