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

主流压力梯度对气膜孔流量系数影响机理

朱惠人 骆剑霞 黄小杨 刘志刚

朱惠人, 骆剑霞, 黄小杨, 刘志刚. 主流压力梯度对气膜孔流量系数影响机理[J]. 航空动力学报, 2014, 29(9): 2142-2149. doi: 10.13224/j.cnki.jasp.2014.09.018
引用本文: 朱惠人, 骆剑霞, 黄小杨, 刘志刚. 主流压力梯度对气膜孔流量系数影响机理[J]. 航空动力学报, 2014, 29(9): 2142-2149. doi: 10.13224/j.cnki.jasp.2014.09.018
ZHU Hui-ren, LUO Jian-xia, HUANG Xiao-yang, LIU Zhi-gang. Influence physics of mainstream pressure gradient on film hole discharge coefficient[J]. Journal of Aerospace Power, 2014, 29(9): 2142-2149. doi: 10.13224/j.cnki.jasp.2014.09.018
Citation: ZHU Hui-ren, LUO Jian-xia, HUANG Xiao-yang, LIU Zhi-gang. Influence physics of mainstream pressure gradient on film hole discharge coefficient[J]. Journal of Aerospace Power, 2014, 29(9): 2142-2149. doi: 10.13224/j.cnki.jasp.2014.09.018

主流压力梯度对气膜孔流量系数影响机理

doi: 10.13224/j.cnki.jasp.2014.09.018
基金项目: 

国家重点基础研究发展计划(2013CB035702)

详细信息
    作者简介:

    朱惠人(1958-),男,陕西西安人,教授、博士生导师,博士,主要从事航空宇航气动传热方向的研究.

  • 中图分类号: V231.1

Influence physics of mainstream pressure gradient on film hole discharge coefficient

  • 摘要: 测量了主流零压力梯度、正压力梯度及负压力梯度条件下气膜孔流量系数,分析了主流压力梯度对气膜孔流量系数的影响机理.结果显示:正、负压力梯度的存在对气膜孔流量系数的影响幅度最大值分别为22%及26%.主流压力梯度会对喷出气流施加弯转作用及挤压作用,同时也会改变喷出气流与近壁面主流的掺混作用,从而影响气膜孔流量系数.挤压作用使喷出气流管变细而增加喷出气流的流动损失;弯转作用主要影响喷出气流的流动轨迹,正压力梯度下弯转作用使喷出气流的轨迹靠近壁面而远离其自由喷射方向增加流动损失,负压力梯度的作用则相反;掺混作用会增加喷出气流的动量消耗,正压力梯度对掺混有抑制作用,从而减少喷出气流用于掺混的动量损失,负压力梯度则相反.

     

  • [1] Hay N,Spencer A.Discharge coefficients of cooling hole with radiused and chamfered inlet[J].Journal of Turbomachinery,1992,114(4):701-706.
    [2] Hay N,Lampard D,Khaldi A.The coefficients of discharge of 30 degree inclined film cooling holes with rounded entries or exits[R].ASME Paper 94-GT-180,1994.
    [3] Burd S W,Simon T W.Measurements of discharge coefficients in film cooling[J].Journal of Turbomachinery,1999,121(2):243-248.
    [4] Hay N,Lampard D.The discharge coefficient of flared film cooling holes[R].ASME Paper 95-GT-15,1995.
    [5] 朱惠人,许都纯,刘松龄.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):42-45. ZHU Huiren,XU Duchun,LIU Songling.The experimental investigation in the effects of film cooling holes shape on discharge coefficient[J].Journal of Propulsion Technology,1998,19(1):42-45.(in Chinese)
    [6] 杨卫华,马国锋,张靖周,等.气膜孔几何结构对流量系数的影响[J].推进技术,2005,26(5):413-416. YANG Weihua,MA Guofeng,ZHANG Jingzhou,et al.Influence of geometrical construction of film cooling hole on discharge coefficient[J].Journal of Propulsion Technology,2005,26(5):413-416.(in Chinese)
    [7] Gritsch M,Schulz A,Wittig S.Discharge coefficient measurements of film-cooling holes with expanded exits[J].Journal of Turbomachinery,1998,120(3):557-563.
    [8] Makki Y H,Jakubowski G.An experimental study of film cooling from diffused trapezoidal shaped holes[R].AIAA 86-1326,1986.
    [9] Gritsch M,Saumweber C,Schulz A,et al.Effect of internal coolant crossflow orientation on the discharge coefficient of shaped film-cooling holes[J].Journal of Turbomachinery,2000,122(1):146-152.
    [10] Roger T,Hersh A S.The effect of grazing flow on the steady state resistance of squared-edged orifices[R].AIAA 75-493,1975.
    [11] Hay N,Lampard D,Benmansour S.Effect of crossflows on the discharge coefficient of film cooling holes[J].Journal of Engineering for Power,1983,105(2):243-248.
    [12] Gritsch M,Schulz A,Wittig S.Effect of crossflow on the discharge coefficient of film cooling holes with varying angles of inclination and orientation[J].Journal of Turbomachinery,2001,123(4):781-787.
    [13] Rowbury D A,Oldfield M L G,Lock G D.Engine representative discharge coefficients measured in an annular nozzle vane cascade[R].ASME Paper 97-GT-99,1997.
    [14] Rowbury D A,Oldfield M L G,Lock G D.Large-scale testing to validate the influence of external crossflow on the discharge coefficients of film cooling holes[J].Journal of Turbomachinery,2001,123(4):593-600.
    [15] 邓明春,朱惠人,王学文,等.密度比对涡轮叶片气膜孔流量系数的影响[J].航空动力学报,2006,21(5):796-799. DENG Mingchun,ZHU Huiren,WANG Xuewen,et al.Influence of density ratio on the discharge coefficient of turbine blade film cooling holes[J].Journal of Aerospace Power,2006,21(5):796-799.(in Chinese)
  • 加载中
计量
  • 文章访问数:  1301
  • HTML浏览量:  0
  • PDF量:  863
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-06-16
  • 刊出日期:  2014-09-28

目录

    /

    返回文章
    返回