加力燃烧室用齿冠状混合器的数值研究与验证

狄虎威; 单勇; 高家春; 张靖周; 刘涛

加力燃烧室用齿冠状混合器的数值研究与验证

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: 1939
- HTML浏览量: 377
- PDF量: 585
- 被引次数: 0
出版历程
- 收稿日期: 2011-09-16
- 刊出日期: 2012-08-28

Numerical study and verification on combustion characteristics of afterburner with chevron mixer

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: 基于CFD(computational fluid dynamics)技术,分别采用有限速率/涡耗散(finite-rate/eddy-dissipation)、涡耗散(eddy-dissipation)和涡耗散概念(EDC)燃烧模型,对一种曲面齿冠状混合器作用下的加力燃烧室进行数值计算.计算结果表明:曲面齿冠状混合器下游产生明显的流向涡对,流向涡的存在可以增强内外涵冷热气流掺混;与直面齿冠状混合器相比,曲面齿冠状混合器下游流向涡强度大于直面齿冠状混合器,其混合效率高于直面齿冠状混合器;加力燃烧室内氧气和二氧化碳质量分数分布结构表明了涡耗散模型的计算更为合理;计算结果可为加力燃烧室混合器选型和燃烧数值模拟提供依据.
- 涡扇发动机 /
- 加力燃烧室 /
- 曲面齿冠状混合器 /
- 燃烧模型 /
- 数值模拟
Abstract: Based on computational fluid dynamics(CFD),the two-phase turbulent combustion in a three-dimensional afterburner with a kind of curved chevron mixer was simulated.Eddy-dissipation,finite-rate/eddy-dissipation and eddy-dissipation-conception models were applied to the combustion simulation,respectively.Numerical results indicate that abundant streamwise vortices,which enhance the mixture between the core flow and bypass flow,form and develop along the downstream of the curved chevron mixer.The intensity of streamwise vortices deduced by curved chevron mixer always is greater than that of the straight chevron mixer.Therefore,the mixing efficiency of curved chevron mixer is the best.The eddy-dissipation model is the most realizable based on the distribution of O₂ and CO₂.
- turbofan engine /
- afterburner /
- curved chevron mixer /
- combustion model /
- numerical simulation

HTML

参考文献(12)

[1]	Skebe S A,Paterson R W,Barber T J.Experimental investigation of three dimensional forced mixer lobe flow fields .AIAA Paper 1988-3785,1988.
[2]	吴川,张靖周,单勇.涡扇-脉冲爆震组合发动机内外涵掺混器研究[J].工程热物理学报,2009,30(8):1437-1439. WU Chuan,ZHANG Jingzhou,SHAN Yong.Mixer investgation of turbofan engine with pulse detonation afterburners[J].Journal of Engineering Thermophysics,2009,30(8):1437-1439.(in Chinese)
[3]	Garrison L A,Lyrintzis A S,Blaisdell G A,et al.Computational fluid dynamics analysis of jets with internal forced mixers .AIAA Paper 2005-2887,2005.
[4]	刘友宏,谢翌,郭楠.尾缘凹扇及综合修行对波瓣混合器性能影响[J].航空动力学报,2010,25(2):243-250. LIU Youhong,XIE Yi,GUO Nan.Effect of elliptical and compositive cut at trailing edge on the performance of a lobed mixer[J].Journal of Aerospace Power,2010,25(2):243-250.(in Chinese)
[5]	Tsui Y Y,Wu P W.Investigation of mixing flow structure in multilobe mixers[J].AIAA Journal,1996,34(7):1386-1391.
[6]	SHAN Yong,ZHANG Jingzhou,XU Liang.Numerical investigation of aeodynamic and mixing characteristics of scarfed lobed mixer for turbofan engine exhaust system[J].Transactions of Nanjing University of Aeronautics and Astronautics,2006,2(20):131-135.
[7]	Mengle V G.Internal flow and noise of chevrons and lobe mixer in mixed-flow nozzles .AIAA Paper 2006-623,2006.
[8]	Bridges J,Wernet M P.Cross-stream PIV measurement of jets with internal lobed mixers .AIAA Paper 2004-2896,2004.
[9]	王亚盟,张靖周,高家春,等.加力燃烧室用锯齿冠状混合器混合特性数值研究[J].航空动力学报,2011,26(1):73-77. WANG Yameng,ZHANG Jingzhou,GAO Jiachun,et al.Numerical study on the mixing characteristics of chevron mixers for the afterburner[J].Journal of Aerospace Power,2011,26(1):73-77.(in Chinese)
[10]	Arai T,Sakaue S,Hiejima H,et al.Streamwise vortices introduced by "hyper-mixer" on supersonic mixing .AIAA Paper 2011-2342,2011.
[11]	刘友宏,谢翌.菊花形混合器混合效率理论计算[J].航空动力学报,2009,24(4):740-744. LIU Youhong,XIE Yi.Analytical solution of mixing efficiency of lobed mixer[J].Journal of Aerospace Power,2009,24(4):740-744.(in Chinese)
[12]	廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2006.