航天推进技术研究院主办
[1]杨事民,唐豪,黄胡.凹腔超声速燃烧室氢气燃烧流场数值模拟[J].火箭推进,2008,34(01):12-16.
Yang Shimin,Tang Hao,Huang Yue.Numerical simulation of hydrogen combustion on flow field in supersonic combustor with cavity[J].Journal of Rocket Propulsion,2008,34(01):12-16.
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Yang Shimin,Tang Hao,Huang Yue.Numerical simulation of hydrogen combustion on flow field in supersonic combustor with cavity[J].Journal of Rocket Propulsion,2008,34(01):12-16.
凹腔超声速燃烧室氢气燃烧流场数值模拟
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年01期
页码:
12-16
栏目:
研究与设计
出版日期:
2008-02-29
- Title:
- Numerical simulation of hydrogen combustion on flow field in supersonic combustor with cavity
- Keywords:
- scramjet; combustion chamber; numerical simulation; cavity structure; fuel injec— fion scheme
- 分类号:
- V235.211
- 文献标志码:
- A
- 摘要:
- 对带长深比为10的凹腔结构的燃烧室二维氢燃烧流场进行数值模拟．燃料喷 注方式采用凹腔上游喷注加辅加凹腔前壁、底壁、后壁喷注。采用三阶MUSCL格式求解二维 含组分守恒N—S方程组，湍流模型采用剪切修正的RNG．|}—F湍流模型，对喷氢燃烧工况进行 了计算研究，并分别分析了凹腔中不同燃料喷注方式对燃烧特性的影响。结果表明：凹腔是 火焰驻留的主要区域；凹腔上游喷注氢，可以使燃料在凹腔中混合燃烧，辅加凹腔中喷氢的 三种方式对燃烧状况产生一定的影响。在凹腔前壁、底面辅加喷氢。没有增强凹腔的稳焰特 性．对整个燃烧状态影响不大；在凹腔后壁喷氢，能够增加凹腔中的燃料含量，加强了回流 效果，对燃烧状态影响较大。三种喷注方式都没有从根本上改变凹腔燃烧流场的特性。
- Abstract:
- The flow fields of hydrogen burning in scramjet combustion chamber witlI length depth ratio cavities were simulated numerically by using the element—-conservation Navier—-Stokes equations with the RNG k—e two—equation turbulence model．The injection schemes are cavity up— stream injection with front wall．bottom and back wall injection assisted．The fuel burning features for different injection schemes were analyzed．The conclusions are as follows：the cavity is the primary area of flame holding；upstream cavity injection of the hydrogen call finish the process of mixing and burning；the assistant injections can affect the flow fields．When adding the injection on front wall and bottom of cavity，the flame holding is not enhanced，and the burning case is scarcely changed；When adding the injection on the back of cavity．it increases the fuel in cavity and strengthens the circumfluence effect．the affect to burning case is obvious．’11le flow fields features are not radically changed by the three assistant injection schemes．
参考文献/References:
[1] Habeeb KM，Kurian J．Cavity Aided Mixing Enhancement
of Supersonic Streams[J]．ISAB 2001-I 189．
[2]Adeh Ben Yaikar,Ronald K Hanson．Cavity Flame Holders
for Ignition and Flame Stabilization in Seramjet：Review
and Experimental StIIdy[R]．ALAA 98-3122．
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for Combustion in Math 1．8 Air-Flow Journal of
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[4]杜炜强，吴宝元．带不同长度凹腔超声速燃烧数值模拟
[J]．火箭推进，2005，31(4)：26-29．
[5]李丽，叶中元，刘兴洲．壁龛稳焰超声速燃烧室流场的数
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[6]胡欲立．超声速燃烧的实验研究与数值模拟[D]．西安：
西北工业大学。1995．
[7]黄生洪，徐胜利，刘小勇．煤油超燃冲压发动机两相流场
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备注/Memo
收稿日期：2007—10．16；修回日期：2007—12—10。基金项目：国家863基金资助项目(2006AA705306)。 作者简介：杨事民(1981一)，男，硕士，研究领域为双模态超燃冲压发动机燃烧室、高超声速流动数值模拟。
更新日期/Last Update:
1900-01-01