探针测量布局对中介机匣流场影响的试验研究  

Experimental investigation for effect of probe measurement position on flowfield of intermediate duct

作　　者：魏崇 向宏辉 刘志刚 赵旺东 赵桓 WEI Chong;XIANG Hong-hui;LIU Zhi-gang;ZHAO Wang-dong;ZHAO Huan(AECC Sichuan Gas Turbine Establishment,Mianyang 621700,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621700

出　　处：《燃气涡轮试验与研究》2020年第5期44-47,62,共5页Gas Turbine Experiment and Research

摘　　要：为研究侵入式常规测量探针对中介机匣气动性能试验的影响,通过更改中介机匣沿气流方向不同轴向位置探针的周向位置,开展了探针布局对中介机匣流场影响的对比试验研究和数值分析。结果表明:中介机匣流道内部探针对下游流场的影响范围很大,影响程度随气流进口马赫数的增大而增大。上游探针尾迹对下游流场影响的轴向距离可达到6.3倍进口流道高度(50倍探针支杆直径),周向影响范围约为4倍探针支杆直径(约15°)。To investigate the influence of normal intrusive probes on the intermediate duct aerodynamic performance test,by changing the circumferential direction of the probes along the axial direction of the axial compressor intermediate duct,experiments and numerical analysis were carried out to investigate the impact of probe layout on the intermediate duct flowfield.The results show that the effect area of probe in the intermediate duct on the downstream flowfield is great,and the impact increases as the Mach number increases.The axial position which probe wake can disturb the downstream flowfield is 6.3 times as the height of the duct(50 times as the diameter of the probe)and circumferentially 4 times as the diameter of the probe(15°).

关 键 词：航空发动机 中介机匣 探针测量布局 流场干扰 试验研究 数值分析 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]