亚声速等膨胀平面射流的初始流场结构  

Initial Flow Structures of an Iso-expanded Subsonic Plane Jet

作　　者：张焕好[1] 陈志华[1] 黄振贵[1] 韩珺礼[1,2] 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094 [2]北京机电研究所,北京100012

出　　处：《推进技术》2012年第4期591-596,共6页Journal of Propulsion Technology

基　　金：高等学校博士学科点专项科研基金(20103219110037);江苏省"青蓝工程"中青年学术带头人培养项目

摘　　要：基于大涡模拟方法与5阶精度混合TCD/WENO格式,对等膨胀射流在马赫数为Ma=0.6条件下的初始流场结构进行了数值模拟。数值结果描述了射流等膨胀过程中,射流初始流场的形成、变化及发展过程。并发现了射流初始流场中涡核为射流失稳的起始点,研究了射流混合层与涡核剪切层上涡的产生、发展与破碎以及它们卷吸环境气体并与射流气体混合的整个过程,揭示了射流初始过程中涡核与涡环直径的变化趋势,得到了射流轴向速度与压力的分布。数值结果可为相关发动机的设计提供重要参考。Based on LES （Large-eddy simulation） , combined with the 5th-order hybrid TCD-WENO scheme, the initial flow field of an iso-expanded subsonic jet at Ma = 0.6 was simulated numerically. The numerical results described the forma- tion, variation and development process of the initial structures of the jet flow. Moreover, it is found that the vortex core is the original source of the jet flow instability, and the generating, developing and breaking processes of the mixing layers of the jet flow and the shear layer of vortex core, and their entrainments of environment gases as well as the mixing processes were stud- ied. The developing tendencies of the vortex ring and its core diameter were shown. The streamwise velocity and pressure dis- tributions of the jet flow along with its symmetrical axis were obtained. The numerical results can provide important guide for some corresponding engine design.

关 键 词：亚声速射流 大涡模拟 涡环 混合层 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]