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Volume 33 Issue 01
Jan.  2007
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Journal of Beijing University of Aeronautics and Astronautics  > 2007  >  33(01): 32-37.
Gong Zhiqiang, Lu Yajun, Li Zhiping, et al. Impact of IGV/rotor interaction on rotor flow field in an axial compressor[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(01): 32-37. (in Chinese)
Citation: Gong Zhiqiang, Lu Yajun, Li Zhiping, et al. Impact of IGV/rotor interaction on rotor flow field in an axial compressor[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(01): 32-37. (in Chinese)
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Impact of IGV/rotor interaction on rotor flow field in an axial compressor

  • National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 13 Jan 2006
  • Publish Date: 31 Jan 2007
    Abstract
  • The IGV/rotor interaction phenomenon in turbomachinery has been resear ch focuses for years, but until now such researches have been restricted to qual itative description of flow phenomenon without theory instructions. So this very important unsteady phenomenon can not be included in turbomachinery design regi me to further improve turbomachinery performance. By the theory of flow instabil ity and receptivity, the rule of using this phenomenon to improve turbomachinery performance can be found. The IGV/rotor interaction phenomenon in a one stage l ow speed axial compressor was investigated experimentally. A 2D digital particle image velocimetry was used to acquire the quantitative flow field structure aro und the rotor with and without IGV. The rotor flow is evidently unsteady even un der steady flow condition. With IGV/rotor interaction, the rotor flow field was changed significantly. The intensity of rotor wakes was reduced, flow separation on rotor suction side was suppressed and the tip leakage flow was suppressed pe riodically. Besides IGV wake interaction and periodic variation in flow angle, d ifferent response of the rotor unsteady flow to different unsteady IGV/rotor exc itation frequency was decided to be the most important reason for the compressor performance changes.

     

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  • [1] Smith L Jr. Casing boundary layers in multistage axial f low compressors. flow research in blading[M]. Amsterdam:I Elsevier Publishin g Company, 1970 [2] Boyd D M, Fleeter S. Rotor blade unsteady aerodynamics at high loading i ncluding dynamic stall . AIAA 2002-3637, 2002 [3] Sirakov B T, Tan C S. Effect of upstream unsteady flow conditions on rot or tip leakage flow . ASME GT2002-30358, 2002 [4] Wu J Z, Vakili A D, Wu J M. Review of the physics of enhancing vortex li ft by unsteady excitation[J]. Prog Aerospace Sci, 1991, 28:73-131 [5] Ahuja K K, Burrin R H. Control of separation by sound . AIAA-84-22 98, 1984 [6] McManus K, Magill J. Airfoil performance enhancement using pulsed jet se paration control . AIAA-97-1971, 1997 [7] 金亮. 非定常激励对压气机时均性能影响的实验研究 . 北京:北京航空航天大学能源与动力工程学院,2005 Jing Liang. Experiment study on the time-mean performance of low speed axia l compressor by unsteady excitation . Beijing:School of Jet Propulsion, Beijing University of Aeronau tics and Astronautics, 2005(in Chinese) [8] Wernet M P, John W T, Prahst P S, et al. Characterization of the t ip clearance flow in a axial compressor using digital PIV . AIAA-2001-0069 7, 2001 [9] Key N L, Lawless P B, Fleeter S. Rotor generated vane row off-design un steady aerodynamics including dynamic stall:part I:stator particle image velov imetry (PIV) investigation . AIAA 2002-3542, 2002 [10] Uzol O, Chow Y C, Katz J, et al. Experimental investigation of unsteady flow field within a two-stage axial turbomachine using particle image velocimet ry[J]. Journal of Turbomachinery, 2002, 124:543-552
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