Volume 26 Issue 3
Mar.  2011
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2011  >  26(3): 543-550
MAO Jun-kui, HU Bo, SU Yun-liang, GUO Wen. Experimental study of the discharge coefficient of film outflow varying with the internal cooling channel’s height[J]. Journal of Aerospace Power, 2011, 26(3): 543-550.
Citation: MAO Jun-kui, HU Bo, SU Yun-liang, GUO Wen. Experimental study of the discharge coefficient of film outflow varying with the internal cooling channel’s height[J]. Journal of Aerospace Power, 2011, 26(3): 543-550.
shu

Experimental study of the discharge coefficient of film outflow varying with the internal cooling channel’s height

  • 1.

    College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • 2.

    Power and Fuel System Design Department, Shanghai Aircraft Design and Research Institute,Shanghai 200232,China

  • 3.

    The Gas Turbine Department,China Gas Turbine Establishment, Aviation Industry Corporation of China,Chengdu 610500,China

  • Received Date: 2010-02-23
  • Rev Recd Date: 2010-10-04
  • Publish Date: 2011-03-28
    Abstract
  • According to the heat transfer enhancement with vortex,experiments were performed to investigate the discharge coefficient of film outflow in narrow confined space,which the ratio of the internal cooling channel height to the diameter of film cooling hole (h/d) was smaller than 1.In experiments,the rules of discharge coefficient Cd varying with the film cooling hole Reynolds number (4800~26000),blowing rate M(0.36~2.74),dimensionless of film cooling channel height h/d(0.33~2.0)were studied in detail,and the similarity criteria for discharge coefficients varying with these parameters were concluded.The experimental results show that the film cooling hole discharge coefficient increase with the film cooling hole Reynolds number when the main flow Reynolds number is constant.In the constant film cooling hole Reynolds number cases,Cd increase with the blowing rate M rising especially when M is smaller than 1.It is also found in experiments that the Cd decrease with dimensionless of film cooling channel height h/d increasing,especially in the cases which the film cooling hole Reynolds number is larger than 9500.

     

    • FullText(HTML)
  • loading
    • References(13)
  • [1]
    侯晓春,季鹤鸣.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,1999:1-9.
    [2]
    Van der Linden S,Gnaedig G,Kreitmeier F.Advanced turbine systems:studies and conceptual design .Morgantown,West Virginia:FE/EE Advanced Turbine Systems Conference,FE Fuel Cells and Coal-Fired Heat Engines Conference,1993.
    [3]
    毛军逵,刘震雄,郭文.小间距单孔冲击凸面靶板流场结构实验[J].航空动力学报,2007,22(10):1598-1603. MAO Junkui,LIU Zhenxiong,GUO Wen.Experimental investigation of a double-decker jet impingement/film structure's cooling coefficient[J].Journal of Aerospace Power,2007,22(10):1598-1603.(in Chinese)
    [4]
    刘震雄,毛军逵,郭文,等.双层壳型冲击/气膜复合冷却效果的实验[J].航空动力学报,2007,22(2):216-221. LIU Zhenxiong,MAO Junkui,GUO Wen,et al.Experiment investigation of a double-decker jet impingement/film structure's cooling coefficient[J].Journal of Aerospace Power,2007,22(2):216-221.(in Chinese)
    [5]
    毛军逵,刘震雄,郭文.小间距冲击凹柱面靶板换热特性实验[J].推进技术,2008,29(2):143-148. MAO Junkui,LIU Zhenxiong,GUO Wen.Experiment of heat transfer on concave surface in single jet impingement cooling system in small jet-to-target space[J]. Journal of Propulsion Technology,2008,29(2):143-148.(in Chinese)
    [6]
    Hay N,Henshall S E,Manning A.Discharge coefficients of hole angled to the flow direction[J].ASME Journal of Turbomachinery,1994,116(1):92-96.
    [7]
    Burd S W,Simon T W.Measurements of discharge coefficients in film cooling[J].ASME J. Turbomach.,1999,121(2):243-248.
    [8]
    Gritsch M,Saumweber C,Sehulz A,et al.Effect of internal coolant crossflow orientation on the discharge coefficient of shaped film-cooling holes[J].ASME Journal of Turbomachinery,2000,122(1):146-152.
    [9]
    方韧,林宇震,李彬,等.燃烧室多斜孔壁流量系数研究[J].航空动力学报,1998,13(1):61-64. FANG Ren,LIN Yuzhen,LI Bin,et al.Discharge coefficients of inclined multi-hole wall cooling in a combustor[J].Journal of Aerospace Power,1998,13(1):61-64.(in Chinese)
    [10]
    Gritsch M,Schulz A,Wittig S.Effect of crossflow s on the discharge coefficient of film cooling holes with varying angles of inclination and orientation[J].Journal of Turbomachinery,2001,123(10):781-787.
    [11]
    朱惠人,许都纯,刘松龄,等.气膜孔形状对流量系数影响的实验研究[J].推进技术,1998,19(1):42-451. ZHU Huiren,XU Duchun,LIU Songling,et al.The investigation in the effects of film cooling holes shape on discharge coefficient[J].Journal of Propulsion Technology,1998,19(1):42-451.(in Chinese)
    [12]
    倪萌,朱惠人,裘云,等.带肋壁与气膜孔内流通道中肋高度对流量系数的影响[J].燃气轮机技术,2004,17(2):30-34. NI Meng,ZHU Huiren,QIU Yun,et al.Effect of rib height on the discharge coefficients of film hole in the internal passage[J].Gas Turbine Technology,2004,17(2):30-34.(in Chinese)
    [13]
    倪萌,朱惠人,裘云,等.肋角度对流量系数影响的数值模拟研究[J] .航空动力学报,2004,19(2):196-200. NI Meng,ZHU Huiren,QIU Yun,et al.Numerical investigation of influence of rib orientation on discharge coefficients[J].Journal of Aerospace Power,2004,19(2):196-200.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 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
    Get Citation
    PDF(1274.0KB)
    XML

    Article Metrics

    Article views (1897) PDF downloads(25) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return