冲击孔对层板冷却叶片前缘传热影响的数值研究

王鸣; 卢元丽; 吉洪湖

冲击孔对层板冷却叶片前缘传热影响的数值研究

1.
中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015
2.
南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2013-07-07
- 刊出日期: 2013-10-28

Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy

1.
Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China
2.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 根据典型涡轮导向叶片型面和边界条件,对简化的层板冷却叶片前缘的流动和传热特性进行数值研究.考察了两种冲击孔与气膜孔和扰流柱的孔阵排布方式、两种冲击孔轴线与靶面的夹角设置方式对叶片前缘换热的影响,计算中采用re-normalization group(RNG)k-ε湍流模型.结果表明:在气膜孔、扰流柱排布一定的条件下,不同冲击孔的模型的冷却流量相差不到1%.冲击孔数目越多和孔径越小的模型的靶面表面传热系数越高;叶片前缘表面的冷却效率越高,提高约2%.在同一种冲击孔孔阵排布方式下,冲击孔轴线和靶面的夹角对流阻和叶片前缘的换热影响不大.
- 层板冷却 /
- 涡轮叶片前缘 /
- 冲击孔 /
- 冷却效率 /
- 表面传热系数
Abstract: According to the typical guide vane shape and the boundary conditions, numerical investigation was carried out to study the flow and heat transfer characteristics on simplified vane leading edge in lamilloy. Two arrangements of impingement holes, film holes and pin-fins, and two axis modes of impingement holes were analyzed, and re-normalization group(RNG)k-ε turbulent model was used. The results show that with the same arrangement of film holes and pin-fins, the models with different impingement holes have less than 1% of cooling flow rate varies. Besides, the model with more impingement holes and smaller diameter of impingement holes can achieve higher heat transfer coefficient and cooling effectiveness, by about 2%. The angle of impingement holes axis has little influence on heat transfer of leading edge in the same arrangement impingement holes.
- lamilloy /
- leading edge of turbine vane /
- impingement hole /
- cooling effectiveness /
- heat transfer coefficient

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参考文献(16)

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