Volume 27 Issue 7
Jul.  2012
Turn off MathJax
Article Contents
ZHANG Bo, LI Wei, DU Qiang, HUANG En-liang, LU Xin-gen, ZHU Jun-qiang. Effect of U-grooves on high-lift low pressure turbine profile's incidence characteristics[J]. Journal of Aerospace Power, 2012, 27(7): 1503-1510.
Citation: ZHANG Bo, LI Wei, DU Qiang, HUANG En-liang, LU Xin-gen, ZHU Jun-qiang. Effect of U-grooves on high-lift low pressure turbine profile's incidence characteristics[J]. Journal of Aerospace Power, 2012, 27(7): 1503-1510.

Effect of U-grooves on high-lift low pressure turbine profile's incidence characteristics

  • Received Date: 2011-08-30
  • Publish Date: 2012-07-28
  • The high-lift low pressure turbine blade profile incidence characteristics under low Reynolds number were investigated.The modification used recessed U-grooves to improve the profiles’ incidence margin.The numerical simulations suggest that compared with high incidence flow condition,lower incidence does not induce large separation which appears on the suction surface of the profile and hence lessens profile loss.The recessed U-grooves delay the separation location,accelerate reattach location,decrease the turbulent wetted area,thereby the separation bubble is suppressed and the profile loss decreases.Whether or not the recessed U-grooves can improve the incidence margin is related to the depth and location of the U-grooves.With±15 incidence degrees,the U-grooves located in 72% axial chord length showed lower profile loss,and when the depth was 0.40mm the profile loss was the lowest.

     

  • loading
  • [1]
    Benner M W,Sjolander S A,Moustapha S H.Measurements of secondary flows downstream of a turbine cascade at off-design incidence .ASME GT 2004-53786,2004.
    [2]
    Benner M W,Sjolander S A,Moustapha S H.Measurements of secondary flows in turbine cascade at off-design incidence .ASME Turbo Expo,GT 97-382,1997.
    [3]
    Jouini D B M,Sjolander S A.Midspan flow-field measurements for two transonic linear turbine cascades at off-design conditions[J].Journal of Turbomachinery,2002,124(2):176-186.
    [4]
    Jouini D B M,Sjolander S A.Off-design performance of a single-stage transonic turbine .ASME GT 2000-0482,2000.
    [5]
    Perdichizzi A,Dossena V.Incidence angle and pitch-chord effects on secondary flows downstream of a turbine cascade[J].Journal of Turbomachinery,1993,115(3):383-391.
    [6]
    孙大伟,乔渭阳,许开富,等.不同攻角涡轮叶栅损失的影响[J].航空动力学报,2008,23(7):1232-1239. SUN Dawei,QIAO Weiyang,XU Kaifu,et al.Influence of different incidences on loss in turbine cascade[J].Journal of Aerospace Power,2008,23(7):1232-1239.(in Chinese)
    [7]
    陈绍文,陈浮,徐文远,等.变攻角下涡轮导向器二次流的实验研究[J].燃气涡轮试验与研究,2005,18(4):15-19. CHEN Shaowen,CHEN Fu,XU Wenyuan,et al.Experimental investigation of secondary flow with different incidences in an LP turbine guide vane[J].Gas Turbine Experimental and Research,2005,18(4):15-19.(in Chinese)
    [8]
    Curtis E M,Hodson H P,Banieghbal M R,et al.Development of blade profiles for low-pressure turbine applications[J].Journal of Turbomachinery,1997,119(3):531-538.
    [9]
    Jame P L,Paul I K,Richard B R.Low Reynolds number loss reduction on turbine blades with dimples and v-grooves .AIAA-2000-0738,2000.
    [10]
    ZHANG Xuefeng,Maria V,Hodson H P.Separation and transition control on an aft-loaded ultra-high-lift LP turbine blade at low Reynolds numbers:low-speed investigation .ASME Paper GT-2005-68892,2005.
    [11]
    蓝吉兵,谢永慧,张荻.低压高负荷燃气透平叶片边界层分离转捩数值模拟与流动控制[J].中国电机工程学报,2009,29(26):68-74. LAN Jibing,XIE Yonghui,ZHANG Di.Numerical simulation and control of separated transition flows in high-lift low-pressure gas turbine cascade[J].Proceedings of the CSEE,2009,29(26):68-74.(in Chinese)
    [12]
    Popovic I,Zhu J,Dai W,et al.Aerodynamics of a family of three highly loaded lower-pressure turbine airfoils:measured effects of Reynolds number and turbulence intensity in steady flow .ASME GT2006-91271,2006.
    [13]
    李伟,朱俊强,李刚,等.基于表面热膜的超高负荷低压涡轮叶栅附面层特性[J].航空动力学报.2011,26(1):115-121. LI Wei,ZHU Junqiang,LI Gang,et al.Experimental research for boundary layer behaviors on an ultra-high-lift low-pressure turbine profile based on surface hot-film[J].Journal of Aerospace Power,2011,26 (1):115-121.(in Chinese)
    [14]
    杜强,朱俊强,温殿中.高负荷低压涡轮边界层转捩预测及其机理分析[J].工程热物理学报,2010,31(5):761-764. DU Qiang,ZHU Junqiang,WEN Dianzhong.Boundary layer transition prediction and mechanism analysis of a high-loading LP turbine blade profile[J].Journal of Engineering Thermophysics,2010,31(5):761-764.(in Chinese)
    [15]
    Benner M W.The effects of leading edge geometry on profile and secondary losses in turbine cascades .Ottawa,Canada:Carleton University,2003.
    [16]
    Denton J D.Loss mechanisms in turbomachines[J].Jornal of Turbomachinery,1993,115(4):621-656.
    [17]
    Robarge T W,Stark A M,Min S K,et al.Design considerations for using indented surface treatments to control boundary layer separation .AIAA 2004-425,2004.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (1769) PDF downloads(618) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return