低马赫数下多凹腔燃烧室非稳态燃烧过程

doi:10.7527/S1000-6893.2016.0149

动力系统

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

低马赫数下多凹腔燃烧室非稳态燃烧过程

王璐^1,2, 高亮杰^1,2, 钱战森^1,2, 赵勇^1,2

1. 中国航空工业空气动力研究院, 沈阳 110034;
2. 高速高雷诺数气动力航空科技重点实验室, 沈阳 110034

收稿日期:2016-04-23 修回日期:2016-05-13 出版日期:2017-01-10 发布日期:2016-05-30
通讯作者: 钱战森,Tel.:024-86566601,E-mail:qianzs@avicari.com.cn E-mail:qianzs@avicari.com.cn
作者简介:王璐,女,硕士,工程师。主要研究方向:燃烧与传热传质。Tel:024-86566632,E-mail:wanglu631@126.com;高亮杰,男,硕士,工程师。主要研究方向:内流空气动力学及推进系统设计。Tel:024-86566632,E-mail:gljnuaa@163.com;钱战森,男,博士,高级工程师。主要研究方向:计算流体力学及高超声速技术。Tel:024-86566601,E-mail:qianzs@avicari.com.cn;赵勇,男,博士,研究员。主要研究方向:叶轮机动力学及设计。Tel:024-86566708,E-mail:m13898857208@163.com
基金资助:
航空科学基金（2014ZA27010）

Unsteady combustion process in multi-cavity combustor at low Mach number condition

WANG Lu^1,2, GAO Liangjie^1,2, QIAN Zhansen^1,2, ZHAO Yong^1,2

1. AVIC Aerodynamic Research Institute, Shenyang 110034, China;
2. Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang 110034, China

Received:2016-04-23 Revised:2016-05-13 Online:2017-01-10 Published:2016-05-30
Supported by:
Aeronsutical Science Foundation of China (2014ZA27010)

摘要/Abstract

摘要：

作为稳定火焰的有效手段之一，凹腔构型在冲压发动机燃烧室研究中占有重要地位。在对以煤油为燃料的多凹腔燃烧室冷/热态流动特性分析的基础上，重点研究低进口马赫数条件下燃烧室点火起动初期非稳态过程。结果表明：上游凹腔内大涡结构有助于提高燃料的驻留时间，未燃混气被高速主流带入下游凹腔内继续反应，进一步提高燃烧效率；燃油喷射速度决定被卷吸进回流区的燃油质量分数的大小，进而影响燃烧效率高低；燃烧室点火起动初期出现了主流熄火、火焰逆流传播以及主流再着火等复杂现象，火焰逆流传播现象是在上游凹腔内燃料自燃与下游燃烧释热压缩来流两种机制共同作用下完成的。

关键词: 低马赫数, 多凹腔燃烧室, 非稳态燃烧, 数值模拟, 喷射

Abstract:

As one of the most effective structures of flame stabilizer, cavity plays an important role in the research on ramjet combustors. Flow field characteristics of the kerosene-fueled multi-cavity ramjet combustor are analyzed without and with combustion in this paper. The unsteady combustion flow field in the combustor is discussed in particular at the initial stage of ignition start-up at low inlet Mach numbers. The results show that the fuel residence time is increased by the bigger vortex in the upstream cavity. The unburned fuel is blown off to the downstream cavity for a further combustion as soon as it meets the high-speed main stream, which is helpful to improve combustion efficiency. The mass of kerosene drifted into cavities is determined by fuel-jet velocity, which would have an indirect effect on the combustion efficiency. At the beginning of the ignition start-up, the phenomena of mainstream blowout, countercurrent flame propagation and mainstream reburning appeared in the unsteady numerical study. The mechanisms of the countercurrent flame propagation are both slow reaction in first cavity and the downstream heat release.

Key words: low Mach number, multi-cavity combustor, unsteady combustion, numerical simulation, jet

中图分类号:

V231.3

王璐, 高亮杰, 钱战森, 赵勇. 低马赫数下多凹腔燃烧室非稳态燃烧过程[J]. 航空学报, 2016, 37(S1): 112-118.

WANG Lu, GAO Liangjie, QIAN Zhansen, ZHAO Yong. Unsteady combustion process in multi-cavity combustor at low Mach number condition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(S1): 112-118.

参考文献

[1] WALTRUP P J. Liquid fueled supersonic combustion ramjets:a research perspective of the past, present and future:AIAA-1986-0158[R]. Reston:AIAA, 1986.
[2] SIKRORIA T, KUSHARI A, SYED S, et al. Experimental investigation of liquid jet breakup in a cross flow of a swirling air stream[J]. Journal of Engineering for Gas Turbines and Power, 2014, 136(6):061501.
[3] CHAULIN A, DANIEL E, CHINNAYYA A, et al. Shock waves in sprays:numerical study of secondary atomization and experimental comparision[J]. Shock Waves, 2015, 26(4):403-415.
[4] LADA C, KONTIS K. Fluidic control of cavity configurations at subsonic and supersonic speeds:AIAA-2005-1293[R]. Reston:AIAA, 2005.
[5] ZHUANG N, ALVI F S, SHIH C. Another look at supersonic cavity flows and their control:AIAA-2005-2803[R]. Reston:AIAA, 2005.
[6] BARNES F W, SEGAL C. Cavity-based flameholding for chemically-reacting supersonic flows[J]. Progress in Aerospace Sciences, 2015,76:24-41.
[7] HSU K, GOSS L, TRUMP D. Performance of a trapped-vortex combustor:AIAA-1995-0810[R]. Reston:AIAA, 1995.
[8] ROQUEMORE W, SHOUSE D, BURRUS D, et al. Vortex combustor concept for gas turbine engines:AIAA-2001-0483[R]. Reston:AIAA, 2001.
[9] JIN Y, HE X, ZHANG J, et al. Experimental study on emission performance of a LPP/TVC[J]. Chinese Journal of Aeronautics, 2012, 25(3):335-341.
[10] ZHANG X, EDWARDS J A. Experimental investigation of supersonic flow over two cavities in tandem[J]. AIAA Journal, 1992, 30(5):1182-1190.
[11] BAO H, ZHOU J, PAN Y, et al. Spark ignition of liquid kerosene in scramjet combustor equipped with partly-covered cavity[J]. Journal of Propulsion and Power, 2015, 31(4):1014-1018.
[12] MCDANIEL J C, CHELLIAH H, GOYNE C P, et al. US national center for hypersonic combined cycle propulsion:an overview:AIAA-2009-7280[R]. Reston:AIAA, 2009.
[13] FETTERHOFF T, BURFITT J. Overview of the advanced propulsion test technology hypersonic aero propulsion clean air test:AIAA-2011-2279[R].Reston:AIAA, 2011.
[14] HASSAN E. Multi-fluid dynamics for supersonic jet-and-crossflows and liquid plug rupture[D]. Ann Arbor:University of Michigan, 2012:25-40.
[15] SEVCENCO Y A, MOJARRAD M G, MARSH R, et al. Integrating hypersonics into a combustion test facility with 3D viewing capability:AIAA-2015-3654[R].Reston:AIAA,2015.
[16] 邓维鑫. 宽范围马赫数超燃冲压发动机燃烧组织技术研究[D]. 成都:西南交通大学, 2013:41-53. DENG W X. Research on combustion organizing technology of scramjet in wide range Mach number[D]. Chengdu:Southwest Jiaotong University, 2013:41-53(in Chinese).
[17] VEYNANTE D, VERVISCH L. Turbulent combustion modeling[J]. Progress in Energy and Combustion Science, 2002(28):193-266.
[18] 中国科学院高超声速科技中心. CASH-001:直联式超声速模型燃烧室[EB/OL]. (2010-03-09)[2016-04-23]. http://www.hrccas.com/newshow.asp?pkid=26.
[19] WILCOX D C. Turbulent modeling for CFD[M]. California:DCW Industries, 2000:74-80.
[20] O'BYRNE S, DOOLAN M, OLSEN S, et al. Analysis of transient thermal choking process in a model scramjet engine[J]. Journal of Propulsion and Power, 2000, 16(5):808-814.
[21] MITANI T, KOUCHI T. Flame structures and combustion efficiency computed for a Mach 6 scramjet engine[J]. Combustion and Flame, 2005, 142(3):187-196.
[22] 潘余. 超燃冲压发动机多凹腔燃烧室燃烧与流动过程研究[D]. 长沙:国防科学技术大学, 2007:23-52. PAN Y. Research on the combustion and flow process in the scramjet multi-cavity combustor[D]. Changsha:National University of Defense Technology, 2007:23-52(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

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

低马赫数下多凹腔燃烧室非稳态燃烧过程

Unsteady combustion process in multi-cavity combustor at low Mach number condition

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	夏侯唐凡, 陈江涛, 邵志栋, 吴晓军, 刘宇. 随机和认知不确定性框架下的CFD模型确认度量综述[J]. 航空学报, 2022, 43(8): 25716-025716.
[2]	杨建凯, 顾冬冬, 葛庆, 檀晨晨, 文雨. 铝合金激光增材制造支撑布局及精确成形机制[J]. 航空学报, 2022, 43(4): 525331-525331.
[3]	吕亚国, 姜乐, 高晓果, 刘振侠, 朱鹏飞, 高文君. 高速轴承环下润滑收油叶片结构参数与工况参数间的匹配关系[J]. 航空学报, 2022, 43(12): 426037-426037.
[4]	姜有旭, 李杰, 杨钊. 某层流机翼验证机风洞试验数据修正方法[J]. 航空学报, 2022, 43(11): 526814-526814.
[5]	段俊亦, 童福林, 李新亮, 刘洪伟. 压缩-膨胀湍流边界层平均摩阻分解[J]. 航空学报, 2022, 43(1): 625915-625915.
[6]	刘朋欣, 袁先旭, 孙东, 傅亚陆, 李辰. 高温化学非平衡湍流边界层直接数值模拟[J]. 航空学报, 2022, 43(1): 124877-124877.
[7]	沈鹏飞, 刘朋欣, 孙东, 袁先旭. 马赫6柱-裙构型激波/湍流边界层干扰摩阻统计特性[J]. 航空学报, 2022, 43(1): 626005-626005.
[8]	刘朋欣, 袁先旭, 梁飞, 李辰, 孙东. 高温化学非平衡湍流边界层脉动量象限分析[J]. 航空学报, 2021, 42(S1): 726338-726338.
[9]	鲍俊, 王瑜, 牛潜, 朱锡冬, 程建杰. 喷雾液滴撞击液膜影响参数及流动机理分析[J]. 航空学报, 2021, 42(S1): 726360-726360.
[10]	陈崇沛, 梁剑寒, 关清帝, 高天运. 守恒型可压缩一维湍流方法及其在超声速标量混合层中的应用[J]. 航空学报, 2021, 42(S1): 726364-726364.
[11]	李青, 涂国华, 余钊圣, 林昭武, 李婷婷, 袁先旭. 惯性颗粒在非均匀加速流中的输运问题[J]. 航空学报, 2021, 42(S1): 726390-726390.
[12]	李成成, 李芳, 杨斌, 王莹. 等离子体激励抑制喷管分离流动数值模拟[J]. 航空学报, 2021, 42(7): 124547-124547.
[13]	刘宗兴, 刘军, 李维娜. 爆炸冲击载荷下典型机身结构动响应及破坏[J]. 航空学报, 2021, 42(2): 224252-224252.
[14]	孙东, 刘朋欣, 沈鹏飞, 童福林, 郭启龙. 马赫数6柱-裙激波/边界层干扰直接模拟[J]. 航空学报, 2021, 42(12): 124681-124681.
[15]	王方, 王煜栋, 姜胜利, 陈军, 唐军, 徐华胜, 李象远, 邢竞文, 高东硕, 金捷. AECSC-JASMIN湍流燃烧仿真软件研发和检验[J]. 航空学报, 2021, 42(12): 625003-625003.