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主流压力梯度对气膜冷却效率影响的数值研究

王玮琪 单勇 廖华琳 谭晓茗 张靖周

王玮琪, 单勇, 廖华琳, 谭晓茗, 张靖周. 主流压力梯度对气膜冷却效率影响的数值研究[J]. 航空动力学报, 2017, 32(8): 1876-1885. doi: 10.13224/j.cnki.jasp.2017.08.012
引用本文: 王玮琪, 单勇, 廖华琳, 谭晓茗, 张靖周. 主流压力梯度对气膜冷却效率影响的数值研究[J]. 航空动力学报, 2017, 32(8): 1876-1885. doi: 10.13224/j.cnki.jasp.2017.08.012
Numerical research on film cooling effectiveness with different mainstream pressure gradient[J]. Journal of Aerospace Power, 2017, 32(8): 1876-1885. doi: 10.13224/j.cnki.jasp.2017.08.012
Citation: Numerical research on film cooling effectiveness with different mainstream pressure gradient[J]. Journal of Aerospace Power, 2017, 32(8): 1876-1885. doi: 10.13224/j.cnki.jasp.2017.08.012

主流压力梯度对气膜冷却效率影响的数值研究

doi: 10.13224/j.cnki.jasp.2017.08.012
基金项目: 国家自然科学基金(51306088); 江苏省自然科学基金(BK20130790); 国家自然科学基金(U1508212)

Numerical research on film cooling effectiveness with different mainstream pressure gradient

  • 摘要: 分别对收缩通道、扩张通道和直通道中亚声速主流条件下的气膜冷却进行数值模拟,对比分析了不同主流压力梯度、次流吹风比条件下的主流和次流流场、温度场特征。研究结果表明:引起气膜冷却效率变化和不同发展趋势的因素可归结为主流边界层厚度、主次流自由剪切混合程度、肾形涡的强度和位置等因素。相对于零压力梯度的主流条件,在吹风比较小(M=0.25)的情况下,主流的逆压力梯度一方面增厚边界层、增强了气膜射流对主流的穿透,另一方面减小了肾形涡的强度,综合作用的结果是气膜平均冷却效率提高了4.91%。在吹风比较大(M=2)的情况下,主流的顺压力梯度扼制主流边界层的发展、抑制气膜射流的穿透能力,降低肾形涡涡核的位置,从而提高气膜冷却效率达17.40%。

     

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出版历程
  • 收稿日期:  2015-12-12
  • 刊出日期:  2017-08-28

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