乙烯简化化学动力学模型在HIFiRE燃烧室计算中的应用

肖保国; 赵慧勇; 杨顺华; 邢建文

doi:10.13224/j.cnki.jasp.2014.06.005

乙烯简化化学动力学模型在HIFiRE燃烧室计算中的应用

doi: 10.13224/j.cnki.jasp.2014.06.005

中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室, 四川绵阳 621000

基金项目:

国家自然科学基金（51376193）

详细信息

作者简介:
肖保国（1980- ），男，湖北红安人，助理研究员，博士，主要从事超燃冲压发动机研究.

中图分类号: V211.3
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- 文章访问数: 2014
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- 被引次数: 0
出版历程
- 收稿日期: 2013-03-26
- 刊出日期: 2014-06-28

Application of reduced chemical kinetic model for ethylene combustion in combustor calculation of HIFiRE

Science and Technology on Scramjet Laboratory, Hypersonic Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 为评估化学反应动力学模型对超燃冲压发动机计算结果的影响，首先利用基于“准稳态”假设方法建立了复杂化学反应动力学模型简化软件包（SPARCK），从详细模型出发得到了一个包含20组分16步总包反应的乙烯简化动力学模型.然后采用该简化模型和Princeton大学的简化模型对乙烯点火延迟时间进行了计算，对比显示两个简化模型计算结果基本一致，与实验测量结果均吻合较好，都能准确反映乙烯点火特性.但对HIFiRE燃烧室直连式实验的数值模拟结果显示两个模型计算得到的燃烧流场静温分布差别较大，内流道推力性能相差近12%.相比于Princeton大学的简化模型，SPARCK软件得到的简化模型计算的壁面压力分布与实验结果吻合更好，能够准确描述燃烧室流场现象.
- 乙烯 /
- “准稳态”假设 /
- 简化化学动力学 /
- 燃烧室 /
- HIFiRE
Abstract: In order to assess the influence of chemical kinetic models on the computational results of scramjet, a software package for reduced chemical kinetics (SPARCK) was used based on quasi-stationary state approximation and specifically developed for chemical reaction kinetics reduction, and a reduced chemical kinetic model with 20 species and 16 global reactions was achieved by reducing the detailed chemical kinetic model for ethylene combustion. Then, the ignition delay time of ethylene was calculated with the reduced model and another reduced model generated by Princeton University. The computational results showed two reduced models almost had the same ignition delay time, and achieved a good agreement with experimental results. Both models can describe the ignition characteristic of ethylene. The Hypersonic International Flight Research Experimentation (HIFiRE) direct-connect test was numerically simulated using two reduced chemical kinetic models. The computational results showed two reduced chemical kinetic models had big difference in the static temperature of combustor, with nearly 12% relative error in the flowpath thrust. The reduced model, obtained by SPARCK, showed better agreement with experimental data for wall pressure distribution, as compared with the Princeton University model, and could simulate accurately combustion phenomena in scramjet combustor.
- ethylene /
- quasi-stationary state approximation /
- reduced chemical kinetics /
- combustor /
- HIFiRE

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参考文献(29)

[1]	Westbrook C K,Dryer F L.Simplified reaction mechanism for the oxidation of hydrocarbon fuels in flames[J].Combustion Science and Technology,1981,27(1/2):31-43.
[2]	Westbrook C K,Dryer F L.Chemical kinetic modeling of hydrocarbon combustion[J].Progress Energy Combustion Science,1984,10:1-57.
[3]	Hautman D J,Dryer F L,Schug K P.A multiple-step overall kinetic mechanism for the oxidation of hydrocarbons[J].Combustion Science and Technology,1981,25(5/6):219-235.
[4]	Eklund R,Baurle R A,Gruber M R.Numerical study of a scramjet combustor fueled by an aerodynamic ramp injector in dual-mode combustion.AIAA 2001-0379,2001.
[5]	Montgomery C J,Cremer M A,Chen J Y,et al.Reduced chemical kinetic mechanisms for hydrocarbon fuels.AIAA-99-2220,1999.
[6]	钱炜祺,杨顺华,肖保国,等.碳氢燃料点火燃烧的简化化学反应动力学模型[J].力学学报,2007,39(1):37-44. QIAN Weiqi,YANG Shunhua,XIAO Baoguo,et al.Development of reduced chemical reaction kinetic model for hydro-carbon fuel combustion[J].Chinese Journal of Theoretical and Applied Mechanics,2007,39(1):37-44.(in Chinese)
[7]	Montgomery C J,Zhao W,Tam C J,et al.CFD simulations of a 3-D scramjet flameholder using reduced chemical mechanisms.AIAA 2004-3874,2004.
[8]	Montgomery C J,Zhao W,Adams B R,et al.Supersonic combustion simulations using reduced chemical kinetic mechanisms and ISAT.AIAA 2003-3547,2003.
[9]	邢建文,郑忠华,宋文艳,等.反应机理对数值模拟超燃冲压发动机性能影响的初步研究.长沙:第十三届激波与激波管学术会议,2008.
[10]	Konnov A A.Implementation of the NCN pathway of prompt-NO formation in the detailed reaction mechanism[J].Combustion and Flame,2009,156(11):2093-2105.
[11]	Wang H,You X,Joshi A V,et al.USC Mech version Ⅱ:high-temperature combustion reaction model of H2/CO/C1-C4 compounds.Combustion Kinetic Laboratory,University of Southern California,2007.http://ignis.usc.edu/USC_Mech_II.htm.
[12]	XU Chaoqi,Konnov A A.Validation and analysis of detailed kinetic models for ethylene combustion[J].Energy,43(1):19-29.
[13]	杨顺华.碳氢燃料超燃冲压发动机数值研究.四川,绵阳:中国空气动力研究与发展中心,2006. YANG Shunhua.Numerical study of hydrocarbon fueled scramjets.Mianyang,Sichuan:China Aerodynamics Research and Development Center,2006.(in Chinese)
[14]	Mawid M A,Sekar B.Kinetic modeling of ethylene oxidation in high speed reacting flows.AIAA 97-3269,1992.
[15]	Baurle R A,Mathur T,Gruber M R,et al.A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications.AIAA 98-3121,1998.
[16]	Law C K,Sung C J,Wang H.Development of comprehensive detailed and reduced reaction mechanism for combustion modeling.AIAA 2002-0331,2002.
[17]	Montgomery C J,Swensen D A,Harding T V,et al.Automated creation and testing of reduced chemical kinetic mechanism.AIAA 2001-3418,2001.
[18]	Warnatz J,Maas U,Dibble R W.Combustion[M].Germany:Springer-Verlag,1999.
[19]	肖保国,钱炜祺,杨顺华,等.甲烷点火燃烧的简化化学反应动力学模型[J].推进技术,2006,27(2):101-105. XIAO Baoguo,QIAN Weiqi,YANG Shunhua,et al.Investigation of reduced chemical reaction kinetic model for combustion of methane[J].Journal of Propulsion Technology,2006,27(2):101-105.(in Chinese)
[20]	杨顺华,肖保国,钱炜祺.乙烯燃烧简化化学动力学模型及其验证[J].实验流体力学,2009,23(2):1-4. YANG Shunhua,XIAO Baoguo,QIAN Weiqi.Reduced chemical kinetics and experimental test for ethylene combustion[J].Journal of Experiments in Fluid Mechanics,2009,23(2):1-4.(in Chinese)
[21]	Storch A M,Bynum M,Liu J,et al.Combustor operability and performance verification for HIFiRE flight 2.AIAA 2011-2249,2011.
[22]	Liu J,Gruber M.Preliminary preflight CFD study on the HIFiRE flight 2 experiment.AIAA 2011-2204,2011.
[23]	Bynum M,Baurle R.A design of experiments study for the HIFiRE flight 2 ground test computational fluid dynamics results.AIAA 2011-2203,2011.
[24]	Cabell K,Hass N,Storch A.HIFiRE direct-connect rig (HDCR) phase I scramjet test results from the NASA Langley arc-heated scramjet test facility.AIAA 2011-2248,2011.
[25]	YANG Shunhua,LE Jialing.Computational analysis of a kerosene-fueled scramjet.ISABE-2005-1195,2005.
[26]	赵慧勇.超燃冲压整体发动机并行数值研究.四川,绵阳:中国空气动力研究与发展中心,2005. ZHAO Huiyong.Parallel numerical study of whole scramjet engine.Mianyang,Sichuan:China Aerodynamics Research and Development Center,2005.(in Chinese)
[27]	Engblom W A,Frate F C,Nelson C C.Progress in validation of WIND-US for ramjet/scramjet combustion.AIAA 2005-1000,2005.
[28]	Liu J,Tam C J,Lu T.Simulations of cavity-stabilized flames in supersonic flows using reduced chemical kinetic mechanisms.AIAA 2006-4862,2006.
[29]	Hidaka Y,Nishimori T,Sato K,et al.Shock-tube and modeling study of ethylene pyrolysis and oxidation[J].Combustion and Flame,1999,117(4):755-776.