航空发动机中介机匣旋涡结构分析  

Vortex Structure Analysis of Intermediate Casing

作　　者：黄旭 雷雨冰[1] HUANG Xu;LEI Yubing(College of Energy and Power Engineering,Nanjing University of Aeronautics And Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2022年第3期213-216,共4页Machine Building & Automation

摘　　要：为了确定某航空发动机中介机匣内部的流场旋涡结构,对其进行数值模拟,采用Q准则对流场进行分析,探索流场中的旋涡结构。研究发现,中介机匣中的旋涡模型主要由马蹄涡、壁角涡、轮毂/支板角区分离涡及机匣出口分离涡等4个旋涡构成。壁角涡与轮毂/支板角区分离涡位于轮毂端壁与支板的角区,主要因为角区的压力场导致了通道内较大的流动损失。机匣出口分离涡由机匣壁面较大的凸曲率产生,导致支板尾缘靠近机匣壁面的流场产生低速区。In order to determine the vortex structure of the flow field inside the intermediate casing of an aeroengine,the numerical simulation was carried out.The Q criterion was used to analyze the flow field and explore the vortex structure in the flow field.It is found that the vortex model in the intermediate casing is mainly composed of horseshoe vortex,corner vortex,hub/branch corner separation vortex and casing outlet separation vortex.Wall corner vortex and corner separation vortex of hub/branch are located in the corner of hub end wall and branch due to the pressure field in the corner area,which leads to large flow loss in the channel.The separation vortex at the outlet of the casing is generated by the larger convex curvature of the casing wall,resulting in the flow field near the tail edge of the branch to produce a low velocity zone.

关 键 词：航空发动机 中介机匣 Q准则 旋涡结构 简化模型 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]