Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor

作     者：Jun Zhang Hongwei Ma Jingyang Li 

作者机构：School of Jet PropulsionBeihang UniversityXueyuan Road 37BeijingChina Shenyang Aeroengine Research InstituteAviation Industry Corporation of ChinaShenyangChina 

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

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

年 卷 期：2012年第21卷第3期

页      码：223-229页

摘      要：This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial compressor. The experiment is carded out in a single-stage large-scale low-speed compressor. The investigated tip geometries include fiat tip as the baseline and suction side squealer tip. The tip clearance of the baseline is 0.5% of the blade span. The static pressure rise characteristic curves of both the rotor and the stage are measured. The flow field at the exit of the rotor is measured by a 5-hole probe under design and off-design conditions. The static pressure on the endwall of the rotor passage is also obtained. The results show that the pressure rise characteristic curves obtained by measuring the pressure on the end wall are almost unchanged by using the suction side squealer tip. The measuring results of the 5-hole probe show the static pressure and the total pressure in tip region is slightly greater than that of the flat tip at the design condition at the exit of the rotor. It also leads to greater averaged static pressure rise and total pressure. At the near stall condition, the averaged static pressure and total pressure is lower than the baseline which is related to the redistribution of the blade load caused by the suction side squealer tip.

主 题 词：Compressor squealer tip 5-hole probe off-design condition tip leakage flow. 

学科分类：082502[082502] 08[工学] 082402[082402] 0824[工学-林业工程类] 0825[工学-环境科学与工程类] 

核心收录：

D　O　I：10.1007/s11630-012-0539-0

馆 藏 号：203688485...