期刊文献+

低雷诺数下跨声速转子周向槽处理机匣扩稳研究 被引量:2

The effects of a transonic compressor rotor with circumferential grooves casing treatment at low Reynolds number
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摘要 采用数值方法模拟了低雷诺数条件下NASA Rotor 37跨声速压气机转子内部流场。结果表明,附面层径向涡是该压气机转子流动失稳的一个很重要的原因。周向槽处理机匣结构对压气机流场的改善较为有限,而引入抽吸处理机匣后,抽吸槽可以将叶顶间隙涡和附面层径向涡及其引发的低能阻塞流团抽吸至处理槽内,叶顶流场大为改善,有效地提高了压气机转子的失速裕度。 The flow instability of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by numerical simulation.Result shows that the boundary layer radial vortex becomes an important factor for triggering off the compressor flow instability.The effects of the transonic compressor rotor with circumferential grooves casing treatment and suction groove casing treatment were investigated.It is showed that the effects of circumferential grooves are not very obvious.The suction groove casing treatment are much more effective,the blockage zones due to boundary layer radial vortex and tip leakage vortex can be suctioned to the suction groove,and the stall margin of the compressor rotor is increased.
出处 《空气动力学学报》 CSCD 北大核心 2011年第2期189-193,共5页 Acta Aerodynamica Sinica
基金 APTD研究项目(APTD-1504-04-07)
关键词 压气机 流动失稳 低雷诺数 机匣处理 附面层径向涡 compressor flow instability low Reynolds number casing treatment boundary layer radial vortex
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参考文献9

  • 1HAH C, ENOMOTO S J , HOBSON G V. Numerical and experimental investigation of low Reynolds number effects on laminar flow separation and transition in a cascade of compressor blade[ R]. ASME Paper, GT - 2000 - 276, 2000.
  • 2HEINZ ADOLF SCHREIBER, WOLFGANG SIEINERT. Effects of Reynolds number and free-stream turbulence on boundary layer transition in a compressor cascade[R]. ASME Paper, GT-21300 -0263, 2000.
  • 3SCHREIBER H A, STEINERT W. Advanced high turning compressor airfoils for low Reynolds number condition. Part2. Experimental and numerical analysis [ R ]. ASME Paper, GT - 2003 - 38417, 2003.
  • 4BEHNKEN R L, et al. Characterizing the effects of air injection on compressor performance for use in active control of rotating stall[ R]. ASME Paper, GT -97 -316, 1997.
  • 5KHALID S. Practiccal compressor casing treatment [ D ]. American Society of Mechanical Engineers. 1997.
  • 6YANG H, NUERNBERGER D, NICKE E A. Numerical investigation of casing treatment mechanisms with a conservation mixed-cell approach [ R]. ASME Paper, GT - 2003 - 28483, 2003.
  • 7LU X, CH W. Mechanism of the interaction between casing treatment and tip leakage flow in a subsonic axial compressor [ R]. ASME Paper, GT -2006 -90077, 2006.
  • 8楚武利,张皓光,吴艳辉,党春宁.槽式处理机匣开槽数目对扩稳效果的影响[J].推进技术,2008,29(5):598-603. 被引量:22
  • 9赵英武.雷诺数对压气机性能影响的数值模拟[D].[硕士学位论文].西安:空军工程大学,2008.

二级参考文献9

  • 1楚武利,卢新根,吴艳辉.带周向槽机匣处理的压气机内部流动数值模拟与试验[J].航空动力学报,2006,21(1):100-105. 被引量:35
  • 2陈海昕,黄旭东,符松.跨声速压气机机匣处理的数值研究[J].航空动力学报,2007,22(2):298-304. 被引量:9
  • 3刘志伟 张长生 黄建功.关于周向槽机匣处理的若干观测.西北工业大学学报,1985,13(1).
  • 4Aamir Shabbir, John J Adamczyk. Flow mechanism for stall margin improvement due to circumferential casing grooves on axial compressors [ R ]. ASME 2004-GT- 53903.
  • 5Rabe D C, Hah C. Application of casing circumferential grooves for improved stall margin in a transonic axial compressor[ R ]. ASME 2002-GT-30641.
  • 6Prince D C J, Wisler D C, Hilvers D E. A study of casing treatment stall margin improvement phenomena [ R ]. ASME 75-GT-60.
  • 7Fujita H, Takata H. A study on configurations of casing treatment for axial flow compressor [ J ]. Bulletin of the JSME, 1984, 27(230) :1675 - 1681.
  • 8Wilke I, Kau H P. A numerical investigation of the influence of casing treatments on the tip leakage flow in a H PC front stage[ R]. ASME 2002-GT-30642.
  • 9Huu Duc Vo,Choon S Tan. Criteria for spike initiated rotating stall[ R ]. ASME 2005-GT-68374.

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