| 气膜孔角度对导叶冷却效果影响的数值研究 |
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| 引用本文： | 姚玉,张靖周,郭文.气膜孔角度对导叶冷却效果影响的数值研究[J].航空动力学报,2009,24(3):507-512. |
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| 作者姓名： | 姚玉 张靖周 郭文 |
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| 作者单位： | 1.南京航空航天大学能源与动力学院, 南京 210016 |
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| 摘 要： | 根据导向叶片的曲面结构,运用SST湍流模型,对涡轮叶栅通道内部的三维流场和圆形气膜孔叶片型面的冷却效果进行了数值模拟,在设计工况下,分析气膜孔倾角的改变对吸力面冷却效果的影响.研究结果为:无论改变哪排气膜孔的倾角,前倾的冷却效果总是高于后倾;相比之下,第一排气膜孔的倾角发生变化后对冷却效果的影响最大.
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| 关 键 词： | 涡轮叶片 喷射角 气膜冷却 数值计算 |
| 收稿时间： | 3/18/2008 3:56:48 PM |
| 修稿时间： | 2008/5/26 0:00:00 |
Numerical investigation on film cooling effectiveness of stator blade with different angles |
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| YAO Yu,ZHANG Jing-zhou and GUO Wen.Numerical investigation on film cooling effectiveness of stator blade with different angles[J].Journal of Aerospace Power,2009,24(3):507-512. |
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| Authors: | YAO Yu ZHANG Jing-zhou and GUO Wen |
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| Institution: | 1.College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China2.China Gas Turbine Establishment, Chengdu 610500, China |
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| Abstract: | The film cooling characteristics on blade surface were numerically investigated using the two-equation turbulence model of the shear-stress transport.Three-dimensional turbulent flow in turbine cascade and the cooling effectiveness on blade surface were carried out under the same coolant total pressure.The influence of the cooling effectiveness of cylindrical film cooling holes on the blade suction surface with varying film hole inclination angles was investigated.Results show that the front inclination of ... |
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| Keywords: | turbine blade injection angle film cooling numerical computation |
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