气膜孔内置扰动条作用下的射流-横流流场

推进技术 ›› 2009, Vol. 30 ›› Issue (1): 30-33.

气膜孔内置扰动条作用下的射流-横流流场

杨成凤,张靖周

南京航空航天大学能源与动力学院;南京航空航天大学能源与动力学院

发布日期:2021-08-15

Investigation of velocity fields in a jet-in-cross-flow by using ridge-shaped tabs

Coll.of Energy and Power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;Coll.of Energy and Power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China

Published:2021-08-15

摘要/Abstract

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。

关键词: 航空、航天推进系统;扰动条;射流;流场

Abstract: 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 penetration close up to the wall.Ridge-shaped tabs may have increased intensity of vortex.The intensity of streamwise vortex pairs is increased as the blow ratio increases,it can improve the mixing of the jet and cross-flow and increase the penetration of spanwise flow as well.

Key words: Aerospace propulsion system;Ridge-shaped tabs;Jet;Velocity fields

杨成凤,张靖周. 气膜孔内置扰动条作用下的射流-横流流场[J]. 推进技术, 2009, 30(1): 30-33.