航天推进技术研究院主办
[1]黄乐萍,豆飞龙,刘昊,等.RBCC燃烧室冲压模态数值模拟及试验验证[J].火箭推进,2022,48(06):69-73,91.
HUANG Leping,DOU Feilong,LIU Hao,et al.Numerical simulation and experimental verification of RBCC combustor in ramjet mode[J].Journal of Rocket Propulsion,2022,48(06):69-73,91.
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HUANG Leping,DOU Feilong,LIU Hao,et al.Numerical simulation and experimental verification of RBCC combustor in ramjet mode[J].Journal of Rocket Propulsion,2022,48(06):69-73,91.
RBCC燃烧室冲压模态数值模拟及试验验证
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年06期
页码:
69-73,91
栏目:
目次
出版日期:
2022-12-25
- Title:
- Numerical simulation and experimental verification of RBCC combustor in ramjet mode
- 文章编号:
- 1672-9374(2022)06-0069-05
- 关键词:
- 火箭基组合循环 燃烧室 冲压模态 煤油
- Keywords:
- RBCC combustor ramjet mode kerosene
- 分类号:
- V235
- 文献标志码:
- A
- 摘要:
- 为了探究煤油燃料火箭基组合循环(RBCC)发动机燃烧室在冲压模态下的燃烧特性,构建了一套仿真计算方法用于预测、分析燃烧室内流动及燃烧过程。以带支板喷注器、单凹腔火焰稳定器RBCC燃烧室为例,开展了冲压模态下的内流场三维数值模拟,计算得到的壁面压力曲线与地面试验及飞行试验结果符合良好。分析燃烧室压力、马赫数、燃气组分等参数可以发现:当前燃烧室结构能够实现冲压模态下液体煤油燃料的稳定、高效燃烧 与冷流相比,压升可达5倍以上 支板能够有效提高煤油燃料的掺混能力 火箭安装台阶下游存在利于燃烧和火焰稳定的回流区 通过调整凹腔、支板等喷注器供油规律,可提高来流氧气的利用率,实现更为充分的燃烧。
- Abstract:
- In order to explore the combustion characteristics of a rocket based combined cycle(RBCC)engine with kerosene in ramjet mode,a numerical simulation method was proposed to predict and analyze the flow and combustion process in the combustion chamber. The 3D internal flow field of a RBCC combustor with strut injectors and a cavity flame holder in ramjet mode were simulated numerically. The calculated wall pressure curve is in good agreement with the results obtained by ground tests and a flight test,indicating that the calculation model is reasonable and practicable. By analyzing the combustor pressure,Mach number,gas composition and other parameters,it can be found that the current combustion chamber structure can realize the stable and efficient combustion of liquid kerosene fuel in ramjet mode. Compared with the cold flow,the pressure rise can reach more than 5 times. The struts can effectively improve the mixing performance of kerosene fuel and air. There is a reflux zone at the downstream of the step for mounting rocket,which is conducive to combustion and flame stability. By adjusting the fuel supply law of injectors such as the cavity and the struts,the utilization rate of inlet oxygen can be improved and more sufficient combustion can be achieved.
参考文献/References:
[1] 张玫,张蒙正,刘昊. 火箭基组合循环动力研究进展[J].科技导报,2020,38(12):54-68.
[2] 刘昊,王君. RBCC发动机火箭推力增益之探讨[J].火箭推进,2017,43(1):18-23.
LIU H,WANG J. Discussion of rocket thrust augmentation for RBCC engine[J].Journal of Rocket Propulsion,2017,43(1):18-23.
[3] 刘昊,王君,张留欢. SMC模式下RBCC发动机4 Ma工况性能仿真[J].火箭推进,2021,47(2):27-31.
LIU H,WANG J,ZHANG L H. Performance simulation of 4 Ma operating condition under SMC mode for RBCC engine[J].Journal of Rocket Propulsion,2021,47(2):27-31.
[4] 张蒙正,李斌,王君,等. 关于RBCC动力系统的思考[J].火箭推进,2013,39(1):1-7.
ZHANG M Z,LI B,WANG J,et al.Thinking about RBCC propulsion system[J].Journal of Rocket Propulsion,2013,39(1):1-7.
[5] 张漫,何国强,刘佩进. RBCC直扩燃烧室煤油喷雾燃烧火焰稳定与放热规律的数值模拟[J].宇航学报,2008,29(5):1570-1576.
[6] ZHANG M,HU Z W,HE G,et al.LES of kerosene spray combustion in RBCC ramjet/scramjet mode[EB/OL].https://www.semanticscholar.org/paper/LES-of-kerosene-spray-combustion-in-RBCC-mode-Zhang-Hu/3f4e639b9e0b 05258a1f2f8ee14cbd6220b31edb,2009.
[7] 潘科玮,何国强,秦飞,等. 煤油燃料RBCC亚燃模态掺混与燃烧数值模拟研究[J].推进技术,2012,33(6):907-913.
[8] VERRTENNICOV V G. Autoignition study on kerosene in supersonic flow[R].F61708-96-WO286,1997.
[9] WANG T S. Thermophysics characterization of kerosene combustion[C]//34th Thermophysics Conference. Reston,Virigina:AIAA,2000.
[10] KUNDU K,PENKO P,YANG S. Reduced reaction mechanisms for numerical calculations in combustion of hydrocarbon fuels[C]//36th AIAA Aerospace Sciences Meeting and Exhibit. Reston,Virginia:AIAA,1998.
[11] 黄生洪,徐胜利,刘小勇. 煤油超燃冲压发动机两相流场数值模拟(I):数值校验及总体流场特征[J].推进技术,2004,25(6):484-490.
[12] STRELETS M. Detached eddy simulation of massively separated flows[C]//39th Aerospace Sciences Meeting and Exhibit. Reston,Virginia:AIAA,2001.
[13] 周力行. 多相湍流反应流体力学[M].北京:国防工业出版社,2002.
[14] WILCOX D C. Turbulence modeling for CFD[M].La Canada,California:DCW Industries,Inc.,1998.
[15] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[16] WANG T S. Thermophysics characterization of kerosene combustion[EB/OL].https://www.semanticscholar.org/paper/Thermophysics-Characterization-of-Kerosene-Wang/0a5bcfd95043e4f39516e0c9f2913a2232bd6965,2000.
[17] 潘科玮,何国强,刘佩进,等. RBCC发动机燃料喷注位置变化对混合燃烧模式燃烧的影响[J].航空动力学报,2011,26(8):1900-1906.
[18] BOUDIER G,GICQUEL L Y M,POINSOT T,et al.Comparison of LES,RANS and experiments in an aeronautical gas turbine combustion chamber[J].Proceedings of the Combustion Institute,2007,31(2):3075-3082.
[19] 陆晋丽.燃烧室结构变化对火箭引射模态性能影响研究[D].西安:西北工业大学,2007.
[20] 汤祥.RBCC支板火箭超燃模态动态过程与性能研究[D].西安:西北工业大学,2015.
[21] WESTBROOK C K,DRYER F L. Simplified reaction mechanisms for the oxidation of hydrocarbon fuels in flames[J].Combustion Science and Technology,1981,27(1/2):31-43.
备注/Memo
收稿日期:2021-11-04 修回日期:2021-11-27
基金项目:国家重点实验室基金项目(6142703190306)
作者简介:黄乐萍(1983—),女,博士,高级工程师,研究领域为组合动力燃烧组织及热防护。
更新日期/Last Update:
1900-01-01