Effects of Probe Support on the Stall Characteristics of a Low-Speed Axial Compressor  

作　　者：Hongwei Ma Shaohui Li Wei Wei 

机构地区：[1]National Key Laboratory of Science and Technology on aero-Engines,Collaborative Innovation Center of Advanced Aero-Engine,School of Energy&Power Engineering,Beihang University,Beijing,100191 China [2]Beijing Institute of Space Launch Technology,Nanyuan Rd.,Fengtai Dist.,Beijing,100076,China [3]China Academy of Aerospace Aerodynamics(CAAA),Yungangxi Rd.,Fengtai Dist.,Beijing,100074,China

出　　处：《Journal of Thermal Science》2016年第1期43-49,共7页热科学学报（英文版）

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

摘　　要：In order to investigate the effects of probe support on the stall characteristics of micro compressors, an experiment was carried out on a large-scale low-speed research compressor according to the principle of geometric similarity. A cylindrical probe support intruding to 50% blade span was mounted at 50% chord upstream from the rotor blade leading edge. The static pressure rise characteristic of the compressor is measured, with and without the probe support respectively. The dynamic compressor behavior from pre-stall to full stall was also measured. The results indicate that the stability margin of the compressor is lowered after installing the probe support. The stall inception is aroused by modal wave disturbances. The disturbances developed into two stall cells smoothly before installing the probe support, while the disturbances first developed into a single stall cell then splitting into two stall cells after installing the probe support. The presence of probe support lowers the initial intensity of the rotating stall of the compressor, while it doesn't alter the intensity of the rotation stall after the compressor enters into full stall.

关 键 词：Probe support Compressor Stability Margin Stall inception Intensity/frequency of rotating stall 

分 类 号：TH453[机械工程—机械制造及自动化]