Affiliation of Author(s):能源与动力学院
Journal:Tuijin Jishu
Abstract:In order to evaluate the effects of inlet probe support on the aerodynamic performance of compressor, the characteristics lines of 1.5-stage compressor including inlet probe support with different diameter, axial position, circumferential position and shape were studied through steady calculation. Results show that, the inlet probe support makes the characteristic lines shift toward the lower left side of those without support employed. The cylindrical support attenuates the lines more seriously than the rectangular one with the same blockage area. And the deviation of the lines increases with increasing the diameter of the support. The average efficiency of the compressor for the 5mm, 10mm and 20mm diameters is reduced by 0.8%, 1.32% and 2.28%, respectively. There is no obvious difference for the lines between supports at different axial position and circumferential position. The steady and unsteady numerical results also demonstrate that, when the inlet flow angle is in the range of insensitive attack angle of the vane, the probe support has no effects on performance of the compressor in the downstream of inlet guide vane by vane rectification. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.
ISSN No.:1001-4055
Translation or Not:no
Date of Publication:2017-05-01
Co-author:Zhao, Jian-Tong,Xiang, Hong-Hui,Gao, Jie
Correspondence Author:Yang Rongfei