留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

轴流压气机叶尖射流扩稳试验

时培杰 乔渭阳 王良锋 陈伟杰 许坤波

时培杰, 乔渭阳, 王良锋, 陈伟杰, 许坤波. 轴流压气机叶尖射流扩稳试验[J]. 航空动力学报, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
引用本文: 时培杰, 乔渭阳, 王良锋, 陈伟杰, 许坤波. 轴流压气机叶尖射流扩稳试验[J]. 航空动力学报, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
SHI Pei-jie, QIAO Wei-yang, WANG Liang-feng, CHEN Wei-jie, XU Kun-bo. Experiment on axial-compressor stability enhancement by blade tip injection[J]. Journal of Aerospace Power, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
Citation: SHI Pei-jie, QIAO Wei-yang, WANG Liang-feng, CHEN Wei-jie, XU Kun-bo. Experiment on axial-compressor stability enhancement by blade tip injection[J]. Journal of Aerospace Power, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018

轴流压气机叶尖射流扩稳试验

doi: 10.13224/j.cnki.jasp.2014.02.018

Experiment on axial-compressor stability enhancement by blade tip injection

  • 摘要: 采用转子叶尖射流对轴流压气机进行了扩稳试验研究.试验中对无射流的轴流压气机失速起始类型进行了测量,发现该轴流压气机以尖峰波的形式进入旋转失速;之后采用叶尖射流发现射流对压气机的失速起始过程没有明显影响.试验中对射流孔数目、射流孔周向分布和射流偏转角3个参数对压气机扩稳效果的影响进行了分析.测量结果发现:保持总射流流量不变,增加射流孔数目会降低轴流压气机扩稳效果;而在单个射流孔流量不变的情况下,增加射流孔数目会增大扩稳效果;射流孔周向分布越均匀扩稳效果越明显;射流扩稳效果与转子相对坐标系下的气动参数有直接关系,故采用相对坐标系下射流零攻角方向的动量分量与主流动量比值对扩稳效果进行了关联.

     

  • [1] 刘大响, 叶培梁, 胡骏, 等.航空燃气涡轮发动机稳定性设计与技术评定[M].北京:航空工业出版社, 2004.
    [2] Schobeiri M T, Attia M.Active control of compressor instability and surge by stator blades adjustment[J].Journal of Propulsion and Power, 2003, 19(2):312-317.
    [3] Crook A J, Greitzer E M, Tan C S, et al.Numerical simulation of compressor endwall and casing treatment flow phenomena[J].Journal of Turbomachinery, 1993, 115(3):501-512.
    [4] Yeung S, Wang Y, Murray R M.Bleed valve rate requirements evaluation in rotating stall control on axial compressors[J].Journal of Propulsion and Power, 2000, 16(5):781-791.
    [5] Nie C Q, Tong Z T, Geng S J, et al.Experimental investigations of micro air injection to control rotating stall[J].Journal of Thermal Science, 2007, 16(1):1-6.
    [6] Nie C Q, Xu G, Chen X B, et al.Micro air injection and its unsteady response in a low-speed axial compressor[J].Journal of Turbomachinery, 2002, 124(4):572-579.
    [7] Weigl H J, Paduano J D, Frechette L G.Active stabilization of rotating stall and surge in a transonic single stage axial compressor[J].Journal of Turbomachinery, 1998, 120(4):625-636.
    [8] Day I J.Active suppression of rotating stall and surge in axial compressors[J].Journal of Turbomachinery, 1993, 115(1):40-47.
    [9] Suder K L, Hathaway M D, Thorp S A, et al.Compressor stability enhancement using discrete tip injection[J].Journal of Turbomachinery, 2001, 123(1):14-23.
    [10] Lim H S, Bae H J, Lim Y C, et al.Injection profile effects on low speed axial compressor stability enhancement[J].Journal of Mechanical Science and Technology, 2011, 25(6):1501-1507.
    [11] Kefalakis M, Papailiou K D.Active flow control for increasing the surge margin of an axial flow compressor[R].ASME Paper 2006-GT-90113, 2006.
    [12] Khaleghi H, Teixeira J A, Tousi A M, et al.Parametric study of injection angle effects on stability of transonic axial compressors[J].Journal of Propulsion and Power, 2008, 24(5):1100-1107.
    [13] 徐纲, 程晓斌, 聂超群, 等.两级低速轴流压气机的喷气试 验的非定常相应[J].工程热物理学报, 2002, 23(1):27-30. XU Gang, CHENG Xiaobin, NIE Chaoqun, et al.Unsteady response to the tip injection in a low-speed axial compressor[J].Journal of Engineering Thermophysics, 2002, 23(1):27-30.(in Chinese)
    [14] 吴艳辉, 楚武利, 张皓光.轴流压气机失速初始扰动的研究进展[J].力学进展, 2008, 38(5):571-584. WU Yanhui, CHU Wuli, ZHANG Haoguang.A review of studies on stall precursors in axial-flow compressor[J].Advances in Mechanics, 2008, 38(5):571-584.(in Chinese)
    [15] Vo H D, Tan C S, Greitzer, E M.Criteria for spike initiated rotating stall[R].ASME Paper 2005-GT-68374, 2005.
    [16] Bennington M A, Cameron J D, Morris S C, et al. Investigation of tip-flow based stall criteria using rotor casing flow visualization[R].ASME Paper 2008-GT-51319.
  • 加载中
计量
  • 文章访问数:  1465
  • HTML浏览量:  3
  • PDF量:  933
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-04-08
  • 刊出日期:  2014-02-28

目录

    /

    返回文章
    返回