| 旋转状态涡轮叶片吸力面单孔气膜冷却实验 |
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| 引用本文： | 李国庆,邓宏武,肖俊.旋转状态涡轮叶片吸力面单孔气膜冷却实验[J].航空动力学报,2010,25(4):780-785. |
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| 作者姓名： | 李国庆 邓宏武 肖俊 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院航空发动机气动热力科技重点实验室,北京,100191 |
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| 摘 要： | 采用稳态液晶测温方法,系统研究了1.5级涡轮叶片吸力面在旋转状态下的气膜冷却特性.实验中,主流经加热压缩后冲击涡轮转动,基于动叶弦长的涡轮进口主流雷诺数为8×104.射流分别采用空气和二氧化碳,其对应射流-主流密度比分别为1.03和1.57.实验转速为630,700 r/min和737 r/min,对应旋转数分别为2.092,2.324和2.448.吹风比从0.3到3.0变化.结果表明,吸力面上,气膜冷却效率随吹风比的增大先上升后下降,存在一个最佳吹风比,使冷却效果最好;增大密度比有利于增加气膜覆盖面积;旋转降低了气膜冷却效率;气膜向低半径方向偏转,但并不十分明显.
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| 关 键 词： | 气膜冷却 涡轮叶片 旋转 冷却效率 密度比 |
| 收稿时间： | 2009/11/2 0:00:00 |
| 修稿时间： | 3/8/2010 12:00:00 AM |
Experimental investigation of rotating single-hole film cooling performance on suction side of a turbine blade |
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| LI Guo-qing,DENG Hong-wu and XIAO Jun.Experimental investigation of rotating single-hole film cooling performance on suction side of a turbine blade[J].Journal of Aerospace Power,2010,25(4):780-785. |
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| Authors: | LI Guo-qing DENG Hong-wu and XIAO Jun |
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| Affiliation: | National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Experimental investigations were carried out to study the rotating film cooling characteristics in a 1.5-stage turbine using stationary thermo liquid crystal method.The length of the test blade in chordwise and spanwise was 124.3 mm and 99 mm respectively with a 4 mm film hole in the middle span oriented 36° to the tangential of the suetion side in streamwise.The mainflow was compressed and heated to bring the turbine to rotate with an inlet Reynolds number Reg of 8×104.Air and CO2 acted as coolant to achieve the coolant to mainflow density ratio of 1.03 and 1.57,respectively.Three rotation numbers of 2.092,2.324 and 2.448 were considered.The blowing ratio varied from 0.3 to 3.0.Results show that on suction side there is an optimum blowing ratio to obtain the best film cooling effectiveness and coverage.Higher density ratio could generate larger film cooling coverage.Rotation is bad for film cooling effectiveness.Meanwhile,the film trajectory deflects centripetally a little due to the horseshoe vortex and rotating effect. |
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| Keywords: | film cooling turbine blade rotating cooling effectiveness density ratio |
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