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低压涡轮叶片内冷通道不同强化换热方案的换热特性
引用本文:张利民,闻洁,丁水汀,陶智,徐国强.低压涡轮叶片内冷通道不同强化换热方案的换热特性[J].航空动力学报,2005,20(4):668-672.
作者姓名:张利民  闻洁  丁水汀  陶智  徐国强
作者单位:北京航空航天大学航空发动机气动热力重点实验室,北京100083
摘    要:利用数值计算和实验相结合的方法,对原型涡轮叶片、改进型叶片和简化后的内冷却通道的模型进行了研究。结果表明,改进的内部冷却通道结构较原型结构冷却效果提高了约7.8%。这种结构改型不但可以强化整个通道的换热,使叶片平均温度降低,同时还可以改善壁面温度的分布,消除局部过热产生的热应力。 

关 键 词:航空、航天推进系统    航空发动机    涡轮叶片    扰流柱    传热
文章编号:1000-8055(2005)04-0668-05
收稿时间:2004/11/15 0:00:00
修稿时间:2004年11月15

Study of Heat Transfer Characteristics of Different Cooling Configurations inside a Typical Low Pressure Turbine Blade
ZHANG Li-min,WEN Jie,DING Shui-ting,TAO Zhi and XU Guo-qiang.Study of Heat Transfer Characteristics of Different Cooling Configurations inside a Typical Low Pressure Turbine Blade[J].Journal of Aerospace Power,2005,20(4):668-672.
Authors:ZHANG Li-min  WEN Jie  DING Shui-ting  TAO Zhi and XU Guo-qiang
Institution:National Key Laboratory of Aircraft Engine, Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract:Numerical simulation and experiment were carried out to study the characteristic of different cooling configurations in a typical low pressure turbine blade.Numerical simulations were performed to investigate the heat transfer of original blade and the improved blades.The numerical results show a good agreement with the experimental ones.Compared to the original blade,the improved blade enhanced the heat transfer effectiveness about 7.8%.The research results indicate that the configuration improving of the inner passage not only reinforces the performance of heat transfer,but also improves temperature distribution and avoids superheated regions.
Keywords:aerospace propulsion system  gas turbine  turbine blade  pin-fin arrays  heat transfer  
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