摘要
对涡轮叶片前缘对冲孔排和错位对冲孔排的气膜冷却特性进行了数值研究,分别在吹风比为0.5、1.0、1.5、2.0的工况下,分析了模型表面气膜冷却效率和表面传热系数的分布规律,对比了不同气膜孔排结构和孔间距对下游气膜冷却效率和传热系数的影响。结果表明:相比于传统同向倾斜孔排结构,对冲孔排结构并没有减弱气膜的冷却特性,反而在靠近端壁处比传统同向倾斜孔排更易于加工;两种孔排下的气膜冷却效率均随着吹风比的增大而减小,而传热系数值均随着吹风比的增大而增大;在孔排近下游范围内,随着孔间距的增大,气膜冷却效率逐渐减小且在小吹风比下更加明显,传热系数值随着孔间距的增大逐渐减小且在大吹风比下更加明显。
Numerical studies were performed for the film cooling performance of counter-inclined film-hole rows,presenting advantage in manufacturing relative to the usually used parallel-inclined film-hole row structure,on a turbine vane leading edge model.Two types of counter-inclined film-hole rows were studied,including collinear counter-inclined film-hole row and non-collinear counter-inclined film-hole row.The distributions of film cooling effectiveness and heat transfer coefficient were obtained for the blowing ratios of 0.5,1.0,1.5 and 2.0.The effect of hole pitch on the film cooling effectiveness and heat transfer coefficient was also studied.Results show that the film cooling performance of counter-inclined film-hole rows is not weakened compared with the traditional parallel-inclined film-hole row structure.The film cooling effectiveness of the two counter-inclined film-hole row structuresdecreases with the increase of blowing ratio,while the heat transfer coefficient increases.The change of inclination structure of film-hole row has very little effect on the heat transfer coefficient in the downstream region,while the increase of hole pitch can influence the values of heat transfer coefficient as well as the film cooling effectiveness in a relatively notable way.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第11期2609-2618,共10页
Journal of Aerospace Power
基金
国家自然科学基金(51306152)
航空科学基金(2014ZB53023)
霍英东教育基金会(141053)
中央高校基本科研业务费专项资金(3102014JCQ01049)
关键词
涡轮叶片
前缘
气膜冷却
对冲孔排
孔间距
turbine vane
leading edge
film cooling
counter-inclined film-hole row
hole pitch
