Effects of Probe Support on the Flow Field of a Low-Speed Axial Compressor

作     者：MA Hongwei LI Shaohui WEI Wei 

作者机构：National Key Laboratory of Science and Technology on Aero-enginesSchool of Energy and Power EngineeringBeihang University 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2014年第23卷第2期

页      面：120-126页

核心收录：

学科分类：080704[工学-流体机械及工程] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0702[理学-物理学] 

基　　金：funded by the National Natural Science Foundation of China Grant No.51161130525 51136003 and the 111 Project No.B07009 

主　　题：probe support compressor 5-hole probe high-response total pressure probe tip leakage flow 

摘      要：This paper presents an investigation on the effect of probe support on the flow field of an axial *** experiment is carried out in a large-scale low-speed research compressor.A cylindrical probe support intruding to 50% blade span was installed at 50% chord upstream from the rotor leading *** region from 5° to 32° off the probe support in the direction of rotation at the rotor outlet was measured with a 5-hole probe and a high-response total pressure *** experiment is performed at both near-design and near-stall *** measuring results of 5-hole probe and high-response total pressure probe indicate that the probe blockage effect is different at different blade *** wake of the probe support weakens the leakage vortex intensity at the tip region,leading to greater total pressure *** near-design condition,the presence of probe support has a negative effect on the region from 75% to 92% span,while improves the flow field below 75% *** near stall condition,the probe support has a negative effect on the region from 70% to 90% span,and almost has no influence on the flow field below 70% span.