面向飞/发一体化设计的高温尾喷口流场分析

doi:10.7527/S1000-6893.2015.0333

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面向飞/发一体化设计的高温尾喷口流场分析

李书¹, 王黎¹, 吴烁¹, 申东¹, 黄瑞², 王强²

1. 北京航空航天大学航空科学与工程学院, 北京 100083;
2. 成都飞机设计研究所结构部, 成都 610031

收稿日期:2015-11-24 修回日期:2015-12-04 出版日期:2016-01-25 发布日期:2015-12-08
通讯作者: 李书,Tel.:010-82314622,E-mail:lishu@buaa.edu.cn E-mail:lishu@buaa.edu.cn
作者简介:李书男,博士,教授,博士生导师。主要研究方向:飞行器设计Tel:010-82314622,E-mail:lishu@buaa.edu.cn;王黎女,硕士。主要研究方向:飞行器设计Tel:010-82316579,E-mail:aewangli@163.com
基金资助:
中航工业产学研专项项目

Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design

LI Shu¹, WANG Li¹, WU Shuo¹, SHEN Dong¹, HUANG Rui², WANG Qiang²

1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China;
2. Structure Department, Chengdu Airplane Design and Research Institution, Chengdu 610031, China

Received:2015-11-24 Revised:2015-12-04 Online:2016-01-25 Published:2015-12-08
Supported by:
AVIC Special Project

摘要/Abstract

摘要：

结合飞/发一体化设计理念,以提升红外隐身性能为目的,引入横向掺混技术进行尾喷管构型设计。应用计算流体力学(CFD)数值仿真方法,分别分析了圆形喷管和矩形喷管流场温度分布,并提取矩形喷管中心面,研究喷管带小孔壁板偏折角对尾流冷却效果的影响。研究结果表明:相对于入口热流温度,矩形喷口降温率约为30%,尾气流喷出后偏向两侧流动,高温核心区体积快速衰减;圆形喷口降温率约为10%,尾气流喷出后沿轴向一直保持圆柱形,高温核心区体积衰减缓慢。矩形喷口主动冷却效果明显高于圆形喷口,更有利于实现飞/发一体化的热管理及红外隐身。同时,中面带小孔壁板偏折角的大小与主动冷却效果也存在密切关系。

关键词: 飞/发一体化设计, 红外隐身, 横向掺混, 主动冷却, 计算流体力学

Abstract:

Combined with the aircraft-engine integration concept,transverse jet mixing technology is introduced to conduct the nozzle design in order to improve infrared stealth performance.The temperature field of circular and rectangular nozzle exhaust flow is analyzed by computational fluid dynamics(CFD) numerical simulation method,and we extract the central face of the rectangular nozzle to observe the cooling effect of transverse jet walls along with different angles.The results show that compared with the inlet temperature,the cooling ratio of rectangular nozzle reaches 30%approximately,the exhaust plume flows to both sides,and the volume of the core high temperature flow decreases obviously;circular nozzle cooling rate is about 10%,the exhaust plume keeps cylindrical along the central line,and the core jet volume attenuation is slow.Consequently,the rectangular nozzle cooling efficiency is significantly higher than that of the circular nozzle and is more advantageous to realize aircraft-engine integrated thermal management as well as infrared stealth.Additionally,active cooling effect also has close relationship with the deflection angle magnitude of the mid wall with transverse jet.

Key words: aircraft-engine integrated design, infrared stealth, transverse mixing, active cooling, CFD

中图分类号:

V221

李书, 王黎, 吴烁, 申东, 黄瑞, 王强. 面向飞/发一体化设计的高温尾喷口流场分析[J]. 航空学报, 2016, 37(1): 364-370.

LI Shu, WANG Li, WU Shuo, SHEN Dong, HUANG Rui, WANG Qiang. Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(1): 364-370.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

面向飞/发一体化设计的高温尾喷口流场分析

Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design

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