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

Zhang Jun ¹ Ma Hongwei ¹ Li Jingyang ²

文摘	This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial compressor.The experiment is carried out in a single-stage large-scale low-speed compressor.The investigated tip geometries include flat 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 av-eraged 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.
来源	Journal of Thermal Science ,2012,21(3):223-229 【核心库】
DOI	10.1007/s11630-012-0539-0
关键词	Compressor ; squealer tip ; 5-hole probe ; off-design condition ; tip leakage flow.
地址	1. School of Jet Propulsion,Beihang University, Beijing 2. Shenyang Aeroengine Research Institute,Aviation Industry Corporation of China, Shenyang
语种	英文
文献类型	研究性论文
ISSN	1003-2169
学科	机械、仪表工业
基金	funded by the National Natural Science Foundation of China ; 国家教育部高等学校学科创新引智计划项目
文献收藏号	CSCD:4532115

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