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

扩压叶栅角区-吸力面造型设计及流动控制机理

李相君 董杰忠 崔义强

李相君, 董杰忠, 崔义强. 扩压叶栅角区-吸力面造型设计及流动控制机理[J]. 航空动力学报, 2020, 35(12): 2642-2653. doi: 10.13224/j.cnki.jasp.2020.12.018
引用本文: 李相君, 董杰忠, 崔义强. 扩压叶栅角区-吸力面造型设计及流动控制机理[J]. 航空动力学报, 2020, 35(12): 2642-2653. doi: 10.13224/j.cnki.jasp.2020.12.018
LI Xiangjun, DONG Jiezhong, CUI Yiqiang. Flow control mechanism of diffuser cascade corner-suction surface profiling design[J]. Journal of Aerospace Power, 2020, 35(12): 2642-2653. doi: 10.13224/j.cnki.jasp.2020.12.018
Citation: LI Xiangjun, DONG Jiezhong, CUI Yiqiang. Flow control mechanism of diffuser cascade corner-suction surface profiling design[J]. Journal of Aerospace Power, 2020, 35(12): 2642-2653. doi: 10.13224/j.cnki.jasp.2020.12.018

扩压叶栅角区-吸力面造型设计及流动控制机理

doi: 10.13224/j.cnki.jasp.2020.12.018
基金项目: 国家自然科学基金青年科学基金(51906027); 辽宁省博士科研启动基金计划(2019-BS-027);中央高校基本科研业务费专项资金资助(3132020112),

Flow control mechanism of diffuser cascade corner-suction surface profiling design

  • 摘要: 通过数值模拟,分别针对扩压叶栅的设计工况与角区失速工况进行叶身/端壁融合与吸力面优化造型设计,分析其流场结构与性能的变化,并探究两种优化造型对压气机性能改善的机理。优化结果表明:在设计工况下,优化造型吸力面凹陷,使得吸力面附面层厚度变薄,最大端壁融合位置靠近尾缘,角区低能流体在压力梯度的作用下转移并减少,分离结构得到明显控制,损失降低;在角区失速工况下,优化造型吸力面凸起,最大端壁融合位置靠近前缘,使得前缘分离结构显著减弱,当流体在进入吸力面前缘时提前附着,前缘分离区减小甚至消失,损失降低。根据两种造型流场结构特点与控制机理,可构造出在多工况下具有显著作用的叶身-端壁融合造型。

     

  • [1] LIU Baojie,AN Guangfeng,YU Xianjun,et al.Experimental investigation of the effect of rotor tip gaps on 3D separating flows inside the stator of a highly loaded compressor stage[J].Experimental Thermal and Fluid Science,2016,75:96-107.
    [2] FEI Teng,JI Lucheng,YI Weilin,et al.Investigation of the dihedral angle effect on the boundary layer development using special-shaped expansion pipes[R].ASME Paper 2018-GT-76383,2018.
    [3] TAYLOR J V,MILLER R J.Competing 3D mechanisms in compressor flows[R].ASME Paper 2015-GT-43322,2015.
    [4] LEI V M,SPAKOVSZKY Z S,GREITZER E M.A criterion for axial compressor hub-corner stall[J].Journal of Turbomachinery,2008,130(3):1-10.
    [5] 李相君,楚武利,张皓光.高负荷轴流压气机叶栅二次流动与损失关联性探讨[J].推进技术,2014,35(7):914-925. LI Xiangjun,CHU Wuli,ZHANG Haoguang.Investi gation on relation between secondary flow and loss on a high loaded axial-flow compressor cascade[J].Journal of Propulsion Technology,2014,35(7):914-925.(in Chinese)
    [6] DEBRUGE L L.The aerodynamic significance of fillet geometry in turbocompressor blade rows[J].Journal of Engineering for Power,1980,102(4):984-993.
    [7] BAGSHAW D A,INGRAM G L,GREGORY-SMITH D G.The design of three-dimensional turbine blades combined with profiled endwalls[J].Power and Energy,2008,222:93-102.
    [8] 彭学敏,季路成,伊卫林,等.高负荷压气机叶栅的叶身/端壁融合研究[J].工程热物理学报,2014,35(2):242-246. PENG Xuemin,JI Lucheng,YI Weilin,et al.Study on blended blade and endwall technique applied to high-load compressor cascades[J].Journal of Engineering Thermophysics,2014,35(2):242-246.(in Chinese)
    [9] SMITH L H,YEH H.Sweep and dihedral effect in axial-flow turbomachinery[J].Journal of Basic Engineering,1963,85(3):401-414.
    [10] BREUGELMANS F A H,CARELS Y,DEMUTH M.Influence of dihedral on the secondary flow in a two-dimensional compressor cascade[J].Journal of Engineering for Gas Turbines and Power,1984,106(3):578-584.
    [11] SASAKI T,BREUGELMANS F.Comparison of sweep and dihedral effects on compressor cascade performance[J].Journal of Turbomachinery,1998,120(3):454-463.
    [12] 季路成,程荣辉,邵卫卫,等.最大负荷设计之:角区分离预测与控制[J].工程热物理学报,2007,28(2):219-222. JI Lucheng,CHENG Ronghui,SHAO Weiwei,et al.Prediction and control of corner separation for in maximizing blade loading[J].Journal of Engineering Thermophysics,2007,28(2):219-222.(in Chinese)
    [13] GMMER V,WENGER U,KAU H P.Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors[J].Journal of Turbomachinery,2001,123(1):40-48.
    [14] 季路成,伊卫林,田勇,等.一种叶轮机械叶片与端壁融合设计方法:CN201010623606.2[P].2011-06-15.
    [15] LI Jiabin,JI Lucheng,YI Weilin.The use of blended blade and end wall in compressor cascade[R].ASME Paper 2018-GT-76048,2018.
    [16] LI Jiabin,JI Lucheng,YI Weilin.Experimental and numerical investigation on the aerodynamic performance of a compressor cascade using blended blade and end wall[R].ASME Paper 2017-GT-63879,2017.
    [17] REUTTER O,POTTMANN S.H,HERGT A,et al.Endwall contouring and fillet design for reducing losses and homogenizing the outflow of a compressor cascade.[R].ASME Paper 2014-GT-25277,2014.
    [18] 李相君.高负荷轴流压气机端区流动机制及被动控制[D].西安:西北工业大学,2018.
  • 加载中
计量
  • 文章访问数:  79
  • HTML浏览量:  1
  • PDF量:  124
  • 被引次数: 0
出版历程
  • 收稿日期:  2020-08-25
  • 刊出日期:  2020-12-28

目录

    /

    返回文章
    返回