探针支杆尾迹特性对压气机叶栅性能的影响  

Effect of probe support wake characteristics on compressor cascade performance

作　　者：高杰 向宏辉 代秋林 幸晓龙 王晖 GAO Jie;XIANG Hong-hui;DAI Qiu-lin;XING Xiao-long;WANG Hui(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)

机构地区：[1]中国航发四川燃气涡轮研究院

出　　处：《燃气涡轮试验与研究》2019年第6期6-13,40,共9页Gas Turbine Experiment and Research

基　　金：四川省科技计划资助项目(2017JY0040);民用飞机专项科研项目(MJ-2016-J-96)

摘　　要：以圆柱状方向探针为研究对象开展了探针支杆尾部椭圆状修型,采用数值模拟与试验研究相结合的方法分析了探针支杆尾迹特性对压气机叶栅性能的影响。结果表明:探针支杆扰流会增大下游叶栅总压损失和对应叶片的尾迹损失;相比于其他安装位置,支杆安装在叶片通道中部时对下游叶栅气动性能的影响较小。当进口马赫数为0.50时,支杆尾部椭圆状修型可以延缓支杆表面附面层气流分离以大幅降低尾迹强度,从而减小尾迹对下游叶栅流场的干扰;当进口马赫数为0.87时,由于支杆表面出现激波与附面层干涉,使得附面层发生分离,此时进行支杆尾部椭圆状修型不能有效降低支杆尾迹强度,无法减小支杆尾迹对下游叶栅流场的干扰。An ellipsoidal reconstruction at the probe support tail edge was developed with a cylindrical di⁃rection probe,and the effect of probe wake characteristics on compressor cascade performance was analyzed by the method of numerical simulation and experimental study.The results show that the disturbance of the probe support will increase the total pressure loss of the downstream cascade and the wake loss of the corre⁃sponding blade.Compared to other probe installation location,the effect of the probe wake disturbance on downstream cascade performance is lower by installing in the middle of blade passage.When the inlet Mach number is equal to 0.50,the reconstruction at the probe support tail could delay the boundary layer separa⁃tion at the support surface to reduce the cascade blade wake strength,accordingly the disturbance to the downstream flow field is reduced.When the inlet Mach number is equal to 0.87,the phenomenon of shock wave boundary layer interference appears at the support surface,so the reconstruction method could not de⁃crease the support wake strength effectively and reduce the disturbance to the downstream cascade flowfield.

关 键 词：航空发动机 压气机叶栅 探针支杆 尾部结构 数值模拟 试验研究 

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]