加力燃烧室用锯齿冠状混合器混合特性数值研究

王亚盟; 张靖周; 高家春; 单勇; 刘涛

加力燃烧室用锯齿冠状混合器混合特性数值研究

1.
南京航空航天大学能源与动力学院,南京 210016
2.
中国航空工业集团公司沈阳发动机设计研究所,沈阳 110015

基金项目: 航空科学基金(2008ZB0607)

计量
- 文章访问数: 1963
- HTML浏览量: 286
- PDF量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2009-12-02
- 修回日期: 2010-01-19
- 刊出日期: 2011-01-28

Numerical study on the mixing characteristics of chevron mixers for the afterburner

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
2.
Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China,Shenyang 110015,China

摘要

摘要: 通过三维计算流体动力学(CFD)数值计算,研究了加力燃烧室中三种不同型式的锯齿冠状混合器及环形混合器的掺混性能.结果表明:①锯齿冠状混合器下游形成了流向涡阵列,锯齿布置和倾角对其尺度和强度有较大的影响;②相邻锯齿交错布置的锯齿冠混合器的强化掺混效果最为显著且流动损失相对较低,总压恢复系数相对环形混合器降低在0.2%以内,在其作用下,加力燃烧室火焰稳定器前的外涵气流温度提高100~150K左右.
- 齿冠状混合器 /
- 加力燃烧室 /
- 掺混 /
- 数值计算 /
- 混合特性
Abstract: Three-dimensional computational fluid dynamics (CFD) computations were conducted to analyze the mixing characteristics of three types of chevron mixers and the confluent mixer used in the afterburner.The research results obtained in the present conditions show that:(1) an array of stream-wise vorticity could be induced by chevron mixers,and the stream-wise vorticity scale and intensity are affected seriously by the chevrons arrangement and inclined angle;(2) the chevron mixer with chevrons tilted alternately inward and outward demonstrates the best performance with higher thermal mixing efficiency and lower extra pressure loss,the total pressure recovery coefficient decreases 0.2% compared to confluent mixer,and the mixing flow temperature increases about 150K in front of flameholder by enhancing the mixing process between core flow and bypass flow.
- chevron mixer /
- afterburner /
- mixing /
- numerical computation /
- mixing characteristics

HTML

参考文献(12)

[1]	Tsui Y Y,Wu P W.Investigation of mixing flow structure in multilobe mixers .AIAA Journal,1996,34(7):1386-1391.
[2]	Salman H,McGnirk J J,Page G J.A numerical study of vortex interactions in lobed mixer flow fields .AIAA Paper 99-3409,1999.
[3]	Liu Y H.Experimental and numerical investigation of circularly lobed nozzle with/without central plug[J].International Journal of Heat and Mass Transfer,2002,45(12):2577-2585.
[4]	张靖周,谢志荣,李立国.三维强迫混合波瓣结构流场的数值研究[J].推进技术,2001,22(3):225-228. ZHANG Jingzhou,XIE Zhirong,LI Liguo.Numerical investigation of three-dimensional flow fields for forced mixer lobe configuration [J].Journal of Propulsion Technology,2001,22(3):225-228.(in Chinese)
[5]	单勇,张靖周.波瓣喷管结构参数对引射混合器性能影响的数值研究[J].航空动力学报,2005,20(6):973-977. SHAN Yong,ZHANG Jingzhou.Numerical investigation on the effects of lobe nozzle geometric parameters on mixer-ejector performance [J].Journal of Aerospace Power,2005,20(6):973-977.(in Chinese)
[6]	Callender B,Gutmark E A.PIV flow investigation of chevron nozzle mechanisms .AIAA Paper 2004-019,2004.
[7]	Booher M E,Okey K,Barta A B.Development of an advanced exhaust mixer for a high bypass ratio turbofan engine .AIAA Paper 93-2435,1993.
[8]	Tew D E,Waitz I A,Hermanson J C.Impact of compressibility on mixing with large-scale streamwise vorticity .AIAA Paper 97-2637,1997.
[9]	Clifford A B,James B.Acoustic efficiency of azimuthal modes in jet noise using chevron nozzles .AIAA Paper 2006-2645,2006.
[10]	左秀娟,黄勇,李永,等.喷管加装小突片强化射流混合的PIV测量[J].推进技术,2004,25(1):15-18. ZUO Xiujuan,HUANG Yong,LI Yong,et al.PIV measurements of the jet flows enhanced by tabs fixed on convergent-divergent (C-D) nozzles [J].Journal of Propulsion Technology,2004,25(1):15-18.(in Chinese)
[11]	陈方,吴寿生,魏福清,等.常压、双涵进气条件下小突片强化混合研究[J].航空动力学报,2002,17(1):35-39. CHEN Fang,WU Shousheng,WEI Fuqing,et al.Investigation on two-flow mixing enhancement by small tabs at atmospheric pressure [J].Journal of Aerospace Power,2002,17(1):35-39.(in Chinese)
[12]	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(2):215-218. WANG Qiang,Eriqitai,YANG Yong.Numerical simulation on three dimensional nozzle flow field with tabs [J].Journal of Propulsion Technology,2001,22(2):215-218.(in Chinese)