摘要
为改善气膜冷却效率,提出了在倾斜气膜孔前缘内置扰动条的结构。通过与典型的圆柱形气膜孔流场的对比研究,总结出内置扰动条对流场的影响规律。研究结果表明,在射流-横流流场中,内置扰动条减小了射流向主流的穿透,使反向旋转涡对向壁面靠拢,穿透顶点下移;扰动条使下游反向涡对的强度增大;随着吹风比的增大,气膜孔下游同一位置处的流向涡强度增大,这一方面增加了主次流的相互掺混,另一方面也增大了流体沿展向的相互掺混。
In order to improve the film cooling effectiveness,the ridge-shaped tabs located along the upstream edge of declining holes were devised.The effect of the ridge-shaped tabs on the penetration and spreading of a jet in a cross-flow has been studied by numerical simulation.The velocity fields have been compared with the typical cylindrical film cooling holes.The results show that ridge-shaped tabs reduce the jet penetration in a jet-cross flow and make the pair of counter-rotating vortices and the peak of pen...
出处
《推进技术》
EI
CAS
CSCD
北大核心
2009年第1期30-33,共4页
Journal of Propulsion Technology
关键词
航空、航天推进系统
扰动条
射流
流场
Aerospace propulsion system
Ridge-shaped tabs
Jet
Velocity fields
