超燃发动机燃烧模态判别准则初步研究

推进技术 ›› 2015, Vol. 36 ›› Issue (8): 1121-1126.

• 总体与系统 • 下一篇

超燃发动机燃烧模态判别准则初步研究

肖保国,晏至辉,田　野,邢建文

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

发布日期:2021-08-15
作者简介:肖保国(1980—)，男，博士，研究领域为超声速燃烧。
基金资助:
国家自然科学基金(51376193)。

Preliminary Study on Criterion of Indentifying Combustion Mode for Scramjet

Science and Technology on Scramjet Laboratory of China Aerodynamics Research and Development Center，Mianyang 621000，China,Science and Technology on Scramjet Laboratory of China Aerodynamics Research and Development Center，Mianyang 621000，China,Science and Technology on Scramjet Laboratory of China Aerodynamics Research and Development Center，Mianyang 621000，China and Science and Technology on Scramjet Laboratory of China Aerodynamics Research and Development Center，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 为建立超燃发动机燃烧模态定量判别准则，针对马赫数3.0，总温1500K，总压2.1MPa的来流，完成了燃烧模态的实验和数值模拟研究。对比分析了不同当量比条件下燃烧室马赫数分布和隔离段激波结构，确定了燃烧模态判别采用的两个压力测点特征位置，研究了燃油增加过程中特征位置壁面压强比值的动态特性。结果表明，随着当量比的增加，燃烧模态由超燃模态转变为亚燃模态，当量比0.6是超燃模态过渡到亚燃模态的转换点。特征位置压比变化率最大时刻的比值1.5可以作为定量判别燃烧模态的依据，当特征位置壁面压强比值小于1.5时为超燃模态，大于1.5时为亚燃模态。

关键词: 超燃发动机；燃烧模态；判别准则；实验；数值模拟

Abstract: In order to construct quantificational criterion of indentifying combustion mode for scramjet，experimental study and numerical simulation were carried out at the inflow Mach number 3.0，stagnation temperature 1500K，stagnation pressure 2.1MPa. Mach number distribution in combustor and shock wave structures in isolator were compared and analyzed for different equivalence ratio. Two characteristic locations，where the wall pressure ratio used to constitute criterion of indentifying combustion mode，have been confirmed. The transformation process of pressure ratio in characteristic location with the fuel increasing was researched. Results show that combustion mode changes from scramjet-mode to ramjet-mode with equivalence ratio increasing，and the transition occurred at the equivalence ratio 0.6. The maximun variation 1.5 of pressure ratio in characteristic location can be used as quantificational criterion of indentifying combustion model. The pressure ratio of scramjet-mode is less than 1.5，and the pressure ratio of ramjet-mode is greater than 1.5.

Key words: Scramjet；Combustion mode；Distinguish criterion；Experiment；Numerical simulation

肖保国,晏至辉,田　野,邢建文. 超燃发动机燃烧模态判别准则初步研究[J]. 推进技术, 2015, 36(8): 1121-1126.

XIAO Bao-guo,YAN Zhi-hui,TIAN Ye,XING Jian-wen. Preliminary Study on Criterion of Indentifying Combustion Mode for Scramjet[J]. Journal of Propulsion Technology, 2015, 36(8): 1121-1126.

参考文献

[1] Chun J, Scheuermann T, Von Wolfersdorf, et al. Experimental Study on Combustion Mode Transition in a Scramjet with Parallel Injection [R]. AIAA 2006-8063.
[2] Matthew L Fotia, James F Driscoll. Experimental Investigation of Ram-Scram-Mode Transition Mechanics [R]. AIAA 2012-5835.
[3] Rocci D S, Kau H-P. Experimental Study on Transition Between Ramjet and Scramjet Modes in a Duel-Modecombustor [R]. AIAA 2003-7048.
[4] Daniel J Micka, Sean M Torrez, James F Driscoll. Heat Release Distribution in a Dual-Mode Scramjet Combustor -Measurements and Modeling [R]. AIAA 2009-7362.
[5] Matthew L Fotia, James F Driscoll. Ram-Scram Transition and Flame/Shock-Train Interactions in a Model Scramjet Experiment [J]. Journal of Propulsion and Power, 2013, 29(1):261-273.
[6] Karen Cabell, Neal Hass, Andrea Storch. HIFiRE Direct-Connect Rig (HDCR) Phase in Scramjet Test Results from the NASA Langley Arc-Heated Scramjet Test Facility [R]. AIAA 2011-2248.
[7] Andrea M Storch, Michael Bynum, Jiwen Liu, et al. Combustor Operatability and Performance Verification for HIFiRE Flight 2 [R]. AIAA 2011-2249.
[8] 曲亮. 超燃冲压发动机燃烧模态分类技术研究[D]. 哈尔滨: 哈尔滨工业大学, 2008.
[9] Pan Yu, Liu Wei-Dong, Wang Zhen-Guo. Investigation on the Combustion Mode Translation of Thermal Choked Scramjet [R]. AIAA 2007-5387.
[10] 李大鹏. 煤油双模态冲压发动机燃烧室工作过程研究[D]. 长沙: 国防科学技术大学, 2006.
[11] 刘昊, 宋文艳, 王靛. 氢燃料双模态燃烧室模态转换[J]. 航空动力学报, 2011, 6 (3):576-581.
[12] 张岩, 朱韶华, 刘刚, 等. 双模态冲压发动机中的模态转换研究综述[J].推进技术, 2013, 34(12):1719-1728.(ZHANG Yan, ZHU Shao-hua, LIU Gang, et al. An Overview on Mode Transition in Dual Mode Ramjet [J]. Journal of Propulsion Technology, 2013, 34(12):1719-1728.)
[13] Shunhua Yang, Jialing Le. Computational Analysis of a Kerosene-Fueled Scramjet [R]. ISABE 2005-1195.
[14] 赵慧勇. 超燃冲压整体发动机并行数值研究[D]. 绵阳: 中国空气动力研究与发展中心, 2005.
[15] 杨顺华. 碳氢燃料超燃冲压发动机数值研究[D]. 绵阳: 中国空气动力研究与发展中心, 2006.
[16] 肖保国. 碳氢燃料简化动力学模型和当地自适应建表方法在超燃并行计算中的应用[D]. 绵阳: 中国空气动力研究与发展中心, 2009.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-05-15；修订日期:2014-07-06。基金项目:国家自然科学基金(51376193)。作者简介:肖保国(1980—),男,博士,研究领域为超声速燃烧。E-mail:xbgxl@163.com

超燃发动机燃烧模态判别准则初步研究

Preliminary Study on Criterion of Indentifying Combustion Mode for Scramjet

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