期刊文献+

Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade 被引量:13

Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade
原文传递
导出
摘要 The tip leakage flow between a blade and a casing wall has a strong impact on compressor pressure rise capability, efficiency, and stability. Consequently, there is a strong motivation to look for means to minimize its impact on performance. This paper presents the potential of passive tip leakage flow control to increase the aerodynamic performance of highly loaded compressor blades. Experimental investigations on a linear compressor cascade equipped with blade winglets mounted to the blade tips have been carried out. Results for a variation of the tip clearance and the winglet geometry are presented. Current results indicate that the use of proper tip winglets in a compressor cascade can positively affect the local aerodynamic field by weakening the tip leakage vortex. Results also show that the suction-side winglets are aerodynamically superior to the pressure-side or combined winglets. The suction-side winglets are capable of reducing the exit total pressure loss associated with the tip leakage flow and the passage secondary flow to a significant degree. The tip leakage flow between a blade and a casing wall has a strong impact on compressor pressure rise capability, efficiency, and stability. Consequently, there is a strong motivation to look for means to minimize its impact on performance. This paper presents the potential of passive tip leakage flow control to increase the aerodynamic performance of highly loaded compressor blades. Experimental investigations on a linear compressor cascade equipped with blade winglets mounted to the blade tips have been carried out. Results for a variation of the tip clearance and the winglet geometry are presented. Current results indicate that the use of proper tip winglets in a compressor cascade can positively affect the local aerodynamic field by weakening the tip leakage vortex. Results also show that the suction-side winglets are aerodynamically superior to the pressure-side or combined winglets. The suction-side winglets are capable of reducing the exit total pressure loss associated with the tip leakage flow and the passage secondary flow to a significant degree.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2013年第3期583-593,共11页 中国航空学报(英文版)
基金 the National Natural Science Foundation of China(Grant No.:51076018) the Fundamental Research Funds for the Central Universities Specialized Research Fund for the Doctoral Program of Higher Education
关键词 Compressor cascade Experimental investigation Tip clearance Tip geometry Tip leakage vortex Compressor cascade Experimental investigation Tip clearance Tip geometry Tip leakage vortex
  • 相关文献

参考文献4

二级参考文献37

  • 1郑国胜,戴韧.轴流风扇叶片端导叶作用的研究[J].工程热物理学报,2006,27(z1):165-168. 被引量:10
  • 2耿少娟,张宏武,朱俊强,黄伟光.喷气对低速轴流压气机转子叶顶区域流动的影响[J].工程热物理学报,2007,28(3):395-398. 被引量:6
  • 3Dring R P, Johslyn H D, Hardin L W. An Investigation of Axial Compressor Rotor Aerodynamics [J]. ASME Journal of Engineering for Power, 1982, 104(1): 84-96.
  • 4Whitcomb R T. A Design Approach and Selected Wind- Tunnel Results at High Subsonic Speeds for Wing-Tip Mounted Winglets [R]. NASA TN D-8260, 1976.
  • 5Inoue M, Kuroumaru M. Structure of Tip Clearance Flow in an Isolated Axial Compressor Rotor [J]. Journal of Turbomachinery, 1989, 111(2): 250-256.
  • 6Freeman, C., "Effect of Tip Clearance on Compressor Stability and Engine Performance," Tip Clearance Effects in Axial Turbomachines, VKI Lecture Series 1985-05, 1985, Brussels.
  • 7Cumpsty, N. A., Compressor Aerodynamics, Longman Group, London, 1988.
  • 8Schrapp, H., Stark, U., Saathoff, H., "Breakdown of Tip Clearance Vortex in a Rotor Equivalent Cascade and in a Single-stage Low-speed Compressor," ASME GT2008- 50195, Proceedings of ASME Turbo Expo, 2008, Berlin, Germany.
  • 9Storer, J. A., Cumpsty, N. A., "Tip Leakage Flow in Axial Compressors," ASME Journal of Turbomachinery, Vol. 113, No. 2, pp. 252-259, 1991.
  • 10Dean, R. C., Jr., "The Influence of Tip Clearance on Boundary Layer Flow in a Rectilinear Cascade," Gas Turbine Laboratory Report 27-3, Massachusetts Institute of Technology, 1954.

共引文献24

同被引文献137

引证文献13

二级引证文献66

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部