| 旋转对带斜肋和双排孔通道孔流量系数影响 |
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| 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. |
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| 作者姓名： | 张魏 李广超 彭大维 王成军 项松 |
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| 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
2. 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;西北工业大学动力与能源学院,西安,710072 |
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| 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.
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| 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 |
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| 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. |
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| Authors: | ZHANG Wei LI Guang-chao PENG Da-wei WANG Cheng-jun and XIANG Song |
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| Institution: | Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China;;Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China;School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China;Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China;;Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China;;Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering,Shenyang 110136,China; |
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| Abstract: | |
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| Keywords: | aircraft engine turbine blade film hole discharge coefficient numerical simulation |
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