小突片强化混合结构三维流场数值模拟

推进技术 ›› 2001, Vol. 22 ›› Issue (3): 215-218.

小突片强化混合结构三维流场数值模拟

王强,额日其太,杨勇

北京航空航天大学动力系!北京100083;北京航空航天大学动力系!北京100083;北京航空航天大学动力系!北京100083

发布日期:2021-08-15

Numerical simulation on three dimensional nozzle flow field with tabs

Dept. of Jet Propulsion, Beijing Univ.of Aeronautics and Astronautics, Beijing 100083,China;Dept. of Jet Propulsion, Beijing Univ.of Aeronautics and Astronautics, Beijing 100083,China;Dept. of Jet Propulsion, Beijing Univ.of Aeronautics and Astronautics, Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 采用Roe通量差分分裂格式对带有小突片的轴对称收扩喷管内外流场进行了数值模拟。小突片形状有三角形和梯形 ,数目为 2个或 4个 ,堵塞比为 0 0 2 ,0 0 4和 0 0 6 ,相对高度为 0 0 8和 0 16 ,安装角分别为 12 0° ,135°和 15 0°。计算结果表明 :在喷管出口安装 2个或 4个小突片能使得喷管下游内外流掺混时间及掺混距离大为缩短 ,而对喷管的推力系数影响不大。采用小突片对于降低喷流噪声和抑制尾喷流红外辐射是非常有利的

关键词: 小突片;射流喷管;喷射混合流;强化混合;三维流;数值仿真

Abstract: The Reynolds-averaged Navier-Stokes equations were solved numerically by Roe’s flux difference splitting scheme for three-dimensional nozzle flow field with tabs. Several geometrical changes of tabs, such as tab shapes, areas, heights and azimuthal angles, are considered. Use of tabs clearly has significant potential to reduce supersonic jet noise and infrared radiation.

Key words: Small tabs;Jet nozzle;Jet mixing flow;Mixing enhancement;Three dimensional flow;Numerical simulation

王强,额日其太,杨勇. 小突片强化混合结构三维流场数值模拟[J]. 推进技术, 2001, 22(3): 215-218.