两类叶型探针对扩压叶栅流场影响的对比  

Comparative Investigation of Two Types of Airfoil Probe Effects on Flowfield in Compressor Cascade

作　　者：向宏辉[1] 任铭林[1] 马宏伟[2] 贺象[2] 姜正礼[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703 [2]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《燃气涡轮试验与研究》2011年第3期26-30,共5页Gas Turbine Experiment and Research

基　　金：航空科学基金资助项目(2008ZD24012)

摘　　要：为评估叶型探针安装结构的流场适应性,采用性能试验与数值模拟的方法,对比研究了两类叶型探针(A类、B类)对扩压叶栅内部流场的影响。结果表明:对于叶栅通道内没有激波的亚声流场环境,A类探针的综合影响程度略小于B类探针,而对于叶栅通道内会形成强激波的跨声流场环境,A类探针的综合影响程度要大于B类探针;两类叶型探针所诱发的绕流涡演化机制基本相同,但B类探针绕流涡尺度更大,在亚声速扩压叶栅中会带来更大的总压损失。In order to evaluate the flowfield applicability of airfoil probe structure, comparative investigation of two types of airfoil probe （type A and type B） effects on flowfield in compressor cascade was carried out using plane cascade performance experiment and three dimensional numerical simulation methods. The results indicated that the synthesized adverse influence degree of type A probe was slightly less than that of type B probe in subsonic flowfield （not appearing the passage shock wave） of compressor cascade, however, the combined adverse influence degree of type A probe was greater than that of type B probe in the transonic flowfield （appearing the strong shock wave） of compressor cascade. The evolutive physics of both the airfoil probes are same, but the vortex scale caused by type B probe was larger, which resulted in much more total pressure loss in subsonic compressor cascade.

关 键 词：叶型探针 扩压叶栅 流场 性能试验 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]