首页 | 本学科首页   官方微博 | 高级检索  
     检索      

旋转对带斜肋和双排孔通道孔流量系数影响
引用本文:张魏,李广超,彭大维,王成军,项松.旋转对带斜肋和双排孔通道孔流量系数影响[J].航空动力学报,2010,25(6):1258-1263.
作者姓名:张魏  李广超  彭大维  王成军  项松
作者单位:1.沈阳航空工业学院 动力与能源工程学院, 辽宁省数字化工艺仿真与试验技术重点实验室,沈阳 110136
摘    要:为了获得工作叶片内部通道布置斜肋情况下的气膜孔流量系数,利用商业软件对带60°肋和双排气膜孔出流的旋转矩形通道内的流场进行了数值模拟.通道入口雷诺为数60 000,罗斯贝数为0,0.11,0.22,气膜孔总出流比0.22.通道静止时,计算结果与实验数据符合较好,左侧孔和右侧孔的流量系数差别不大.通道顺时针旋转时,两个孔的平均流量系数增加90%左右,左侧孔流量系数是右侧孔流量系数的4~5倍.通道逆时针旋转时,两个孔的平均流量系数减小10%左右,左侧孔和右侧孔流量系数基本相同. 

关 键 词:航空发动机    涡轮叶片    气膜孔    流量系数    数值模拟
收稿时间:5/5/2009 12:00:00 AM
修稿时间:2009/12/23 0:00:00

Influence of rotation on discharge coefficients of two rows of film holes in channel with rib turbulators
ZHANG Wei,LI Guang-chao,PENG Da-wei,WANG Cheng-jun and XIANG Song.Influence of rotation on discharge coefficients of two rows of film holes in channel with rib turbulators[J].Journal of Aerospace Power,2010,25(6):1258-1263.
Authors:ZHANG Wei  LI Guang-chao  PENG Da-wei  WANG Cheng-jun and XIANG Song
Institution:1.Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China2.School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China
Abstract:In order to understand the bleed performance of the film hole on the internal tunnel within the blade,the influence of the rotation on the discharge coefficients of film holes in rectangular channel with both rib-roughened wall and two rows of film hole suctions was studied by numerical simulation at Reynolds number 60000,rotation number 0,0.11 and 0.22,and suction ratio of 0.22.The numerical results agreed well with the experimental data in the stationary passages.The averaged discharge coefficients of the two holes increase by 90% in the clockwise rotating channel and decrease by 10% in the counter-clockwise channel.The discharge coefficients of the left holes are 4~5 times the right holes in the event of clockwise rotation.The discharge coefficients of the left holes and the right holes differ little in the event of counter-clockwise rotation.? 
Keywords:aircraft engine  turbine blade  film hole  discharge coefficient  numerical simulation
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号