| Experiments of flow and heat transfer performances for air-cooling laminated turbine vane |
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| 作者姓名： | WU Xiang-yu TAO Zhi DU Zhi-neng ZHANG Shu-lin YOU Hong-de |
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| 作者单位： | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China |
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| 摘 要： | Flow resistance and heat transfer coefficients of typical double wall laminated film cooling configuration within a turbine vane were experimentally studied.The specimen was in large scale,and made of transparent organic glass.Laminated configuration consisted of double wall laminates,pin-fins,staggered arrays of impingement and film holes.The number ratio of impingement holes,pin-fins and film holes was2∶1∶1.Five experiment vanes were installed in static cascade,and experiments were carried out under constant heat flux.Re of internal cooling air in the experiment was from 104 to 2×105,and Re of external fluid was from 105 to 3×105.The experiment results show that flow resistances of front channel and back channel of the vane are in the same level,and both of them decrease as Re of cooling air increases.Nuof front channel is slightly higher than that of back channel.Both of them increase as Re of cooling air increases.And experiment results were obtained from experiment vanes were compared with that obtained from laminated flat plates,and the tendency of the results agrees well.
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| 关 键 词： | lamilloy turbine vane flow performance heat transfer static cascade |
| 收稿时间： | 2013/12/24 0:00:00 |
Experiments of flow and heat transfer performances for air-cooling laminated turbine vane |
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| WU Xiang-yu,TAO Zhi,DU Zhi-neng,ZHANG Shu-lin,YOU Hong-de.Experiments of flow and heat transfer performances for air-cooling laminated turbine vane[J].Journal of Aerospace Power,2014,29(5):1008-1013. |
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| Authors: | WU Xiang-yu TAO Zhi DU Zhi-neng ZHANG Shu-lin and YOU Hong-de |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China |
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| Abstract: | Flow resistance and heat transfer coefficients of typical double wall laminated film cooling configuration within a turbine vane were experimentally studied. The specimen was in large scale, and made of transparent organic glass. Laminated configuration consisted of double wall laminates, pin-fins, staggered arrays of impingement and film holes. The number ratio of impingement holes, pin-fins and film holes was 2:1:1. Five experiment vanes were installed in static cascade, and experiments were carried out under constant heat flux. Re of internal cooling air in the experiment was from 104 to 2×105, and Re of external fluid was from 105 to 3×105. The experiment results show that flow resistances of front channel and back channel of the vane are in the same level, and both of them decrease as Re of cooling air increases. Nu of front channel is slightly higher than that of back channel. Both of them increase as Re of cooling air increases. And experiment results were obtained from experiment vanes were compared with that obtained from laminated flat plates, and the tendency of the results agrees well. |
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| Keywords: | lamilloy turbine vane flow performance heat transfer static cascade |
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