Authors: Hongwei Ma Shaohui Li Wei Wei
Publish Date: 2014/03/11
Volume: 23, Issue: 2, Pages: 120-126
Abstract
This paper presents an investigation on the effect of probe support on the flow field of an axial compressor The experiment is carried out in a largescale lowspeed research compressor A cylindrical probe support intruding to 50 blade span was installed at 50 chord upstream from the rotor leading edge The region from 5° to 32° off the probe support in the direction of rotation at the rotor outlet was measured with a 5hole probe and a highresponse total pressure probe The experiment is performed at both neardesign and nearstall points The measuring results of 5hole probe and highresponse total pressure probe indicate that the probe blockage effect is different at different blade spans The wake of the probe support weakens the leakage vortex intensity at the tip region leading to greater total pressure rise At neardesign 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 span At 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
Keywords: