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.
According to the typical guide vane shape and the boundary conditions, nu merical 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 pinfins, and two axis modes of impingement holes were analyzed, and renormalization group （RNG） ks turbulent model was used. The results show that with the same arrange ment of film holes and pinfins, 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 effec tiveness, by about 2%. The angle of impingement holes axis has little influence on heat transfer of leading edge in the same arrangement impingement holes.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第10期2240-2247,共8页
Journal of Aerospace Power
关键词
层板冷却
涡轮叶片前缘
冲击孔
冷却效率
表面传热系数
lamilloy
leading edge of turbine vane
impingement hole
cooling effectiveness
heat transfer coefficient
