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

IMR OpenIR

	Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor
其他题名	Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor
	Zhang Jun 1; Ma Hongwei 1; Li Jingyang 2
	2012
发表期刊	JOURNAL OF THERMAL SCIENCE
ISSN	1003-2169
卷号	21 期号:3 页码:223-229
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 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 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.
其他摘要	This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial compressor.The experiment is 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.
关键词	Compressor squealer tip 5-hole probe off-design condition tip leakage flow
收录类别	CSCD
语种	英语
资助项目	[National Natural Science Foundation of China] ; [111 Project]
CSCD记录号	CSCD:4532115
引用统计	被引频次：2[CSCD] [CSCD记录]
文献类型	期刊论文
条目标识符	http://ir.imr.ac.cn/handle/321006/151092
专题	中国科学院金属研究所
作者单位	1.北京航空航天大学 2.中国科学院金属研究所
推荐引用方式 GB/T 7714	Zhang Jun,Ma Hongwei,Li Jingyang. Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor[J]. JOURNAL OF THERMAL SCIENCE,2012,21(3):223-229.
APA	Zhang Jun,Ma Hongwei,&Li Jingyang.(2012).Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor.JOURNAL OF THERMAL SCIENCE,21(3),223-229.
MLA	Zhang Jun,et al."Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor".JOURNAL OF THERMAL SCIENCE 21.3(2012):223-229.