摘要
在兼顾气膜冷却效率的条件下,为了降低气膜冷却带来的气动损失,采用数值模拟的方法研究了双射流孔和收缩型双射流孔的气膜冷却特性。对比分析了不同吹风比(0.5~2.0)工况下气膜冷却效率和损失分布规律。结果表明:当吹风比高于1.0时,收缩型双射流孔促进冷气横向发展,冷却效率提高;当吹风比增加到2.0时,收缩型双射流孔可以防止冷气吹离壁面。与双射流孔相比,收缩型双射流孔入口冷气均匀加速,消除了孔内低速区造成的堵塞,流场趋于均匀,孔内损失明显降低,从而整体上降低了气膜冷却引起的总压损失。
Film cooling characteristics and loss mechanism of double-jet hole and contracted doublejet hole with blowing ratio varying from 0.5 to 2.0 were numerically simulated.Results showed that the lateral film coverage developed and the film cooling effectiveness was promoted for the Contracted Double-jet hole when the blowing ratio was bigger than 1.0.When the blowing ratio reached 2.0,the Contracted Double-jet hole can prevent the film lift-off.Compared with the Double-jet hole,the cooling flow at the inlet of the Contracted Double-jet hole was accelerated evenly and the blockage caused by the low velocity zone in the hole was eliminated so that the flow field became uniform and the total pressure loss was reduced.
作者
康忠
李国庆
张深
王晓东
张燕峰
卢新根
KANG Zhong;LI Guoqing;ZHANG Shen;WANG Xiaodong;ZHANG Yanfeng;LU Xingen(Laboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Energy,Power and Mechanical Engineering,North China Electric Power University,Beijing 102206,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2023年第2期335-343,共9页
Journal of Aerospace Power
基金
国家自然科学基金(51976214)。
关键词
气膜冷却
气膜冷却效率
总压损失
气膜孔
损失机理
film cooling
film cooling effectiveness
total pressure loss
film cooling hole
loss mechanism
