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致密孔阵气膜冷却绝热温比和对流换热系数的数值研究

Numerical study on adiabatic wall cooling effectiveness and convective heat transfer coefficient of effusion cooling

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【作者】 谢浩张靖周

【Author】 XIE Hao1,2,ZHANG Jing-zhou2(1.School of Power Engineering,Nanjing Normal University,Nanjing 210042,China;2.College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

【机构】 南京师范大学动力工程学院南京航空航天大学能源与动力学院

【摘要】 采用数值模拟方法研究了气膜孔叉排方式下孔间距和吹风比对致密孔阵气膜冷却绝热温比和对流换热系数的影响.结果表明:减小相邻孔间距与孔径比或增加吹风比,平均壁面温度就越低,且温度分布更为均匀,绝热温比提高,热侧壁面平均换热系数也随之增大;相对于增加气膜孔阵的密集程度而言,吹风比的增加所带来的绝热温比改善和对流换热系数增加幅度略有减弱.特别是当吹风比大于1以后,吹风比的影响程度比较微弱.

【Abstract】 The influences of the adjacent holes spacing and blowing ratio on the adiabatic wall cooling effectiveness and convective heat transfer coefficient of effusion cooling with the film holes in staggered arrangement were numerically investigated.The results show that,with the decrease of adjacent holes spacing or the increase of blowing ratio,the average temperature in the film holes region reduces and the temperature distribution uniformity is improved for all the calculated cases,so that the adiabatic wall cooling effectiveness increases along with the convective heat transfer coefficient.In relation to the decrease of adiabatic holes spacing,the influence of blowing ratio increase is not obvious,especially when the blowing ratio is greater than 1,the influence becomes very weaker.

【基金】 航空科学基金(03C52019)
  • 【文献出处】 航空动力学报 ,Journal of Aerospace Power , 编辑部邮箱 ,2009年06期
  • 【分类号】V231.1
  • 【被引频次】15
  • 【下载频次】300
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