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涡轮叶片前缘对冲孔排气膜冷却特性的数值研究

赵丹 刘存良 朱惠人 翟颖妮

赵丹, 刘存良, 朱惠人, 翟颖妮. 涡轮叶片前缘对冲孔排气膜冷却特性的数值研究[J]. 航空动力学报, 2017, 32(11): 2609-2618. doi: 10.13224/j.cnki.jasp.2017.11.007
引用本文: 赵丹, 刘存良, 朱惠人, 翟颖妮. 涡轮叶片前缘对冲孔排气膜冷却特性的数值研究[J]. 航空动力学报, 2017, 32(11): 2609-2618. doi: 10.13224/j.cnki.jasp.2017.11.007
Numerical studies on film cooling performance of turbine vane leading edge with counter-inclined structure[J]. Journal of Aerospace Power, 2017, 32(11): 2609-2618. doi: 10.13224/j.cnki.jasp.2017.11.007
Citation: Numerical studies on film cooling performance of turbine vane leading edge with counter-inclined structure[J]. Journal of Aerospace Power, 2017, 32(11): 2609-2618. doi: 10.13224/j.cnki.jasp.2017.11.007

涡轮叶片前缘对冲孔排气膜冷却特性的数值研究

doi: 10.13224/j.cnki.jasp.2017.11.007
基金项目: 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)

Numerical studies on film cooling performance of turbine vane leading edge with counter-inclined structure

  • 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。

     

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出版历程
  • 收稿日期:  2016-04-19
  • 刊出日期:  2017-11-28

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