中心支板式RBCC发动机引射模态流动与燃烧研究

doi:10.13675/j.cnki.tjjs.200173

推进技术 ›› 2020, Vol. 41 ›› Issue (10): 2292-2301.DOI: 10.13675/j.cnki.tjjs.200173

中心支板式RBCC发动机引射模态流动与燃烧研究

石磊，赵国军，杨一言，秦飞，魏祥庚，何国强

西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072

发布日期:2021-08-15
基金资助:
国家自然科学基金（51976171；51606156）。

Flow and Combustion of Central-Strut Based RBCC Engine in Ejector Mode

Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了深入认识引射模态工作机理，针对中心支板式RBCC发动机，在飞行马赫数2、不同内置火箭流量时的工作情况进行了全流道一体化的数值模拟，并对其内流场特征、火箭射流/引射空气掺混发展特征以及复合型释热规律和火焰结构等开展了详细分析。研究发现：RBCC发动机引射模态下的流动掺混燃烧过程是一个复杂且高度耦合的过程。在即时预混燃烧（SMC）模式下，燃烧过程主要在内置火箭射流与来流空气之间形成的剪切层内进行；流道上游剪切层厚度较薄，温度和组分浓度梯度较大，掺混速率快；高释热区集中分布在流道上游，可分为超声速释热区和亚声速释热区；流道内的燃烧反应以扩散燃烧为主，随着掺混过程的进行逐渐向预混燃烧过渡。提高火箭流量，流道内温度升高，反应持续距离增加，但掺混效率降低。

关键词: 组合循环发动机;引射模态;燃烧;空气引射;掺混;预混燃烧

Abstract: In order to realize a deeper understanding of the operational mechanism in the ejector mode， fully channel integrated numerical simulations were carried out on a central-strut based RBCC engine within different built-in rocket operational conditions at a typical flight Mach number of 2. In detail， the internal flow characteristics， the mixing and development characteristics of rocket jet and entrained air， as well as the heat release and flame structure were analyzed. It has been found that the mixing and combustion process in the RBCC engine adopting the Simultaneous Mixing and Combustion（SMC） cycle in the ejector mode was a complex and highly coupled process. In SMC combustion mode， the combustion was mainly carried out in the shear layer formed between the built-in rocket jet and the incoming air. The thickness of the shear layer at the upstream of the flow channel was thinner， the gradients of temperature and component concentration were larger， and the mixing rate was higher. The high heat release zone was mainly distributed in the upstream of the channel， which could be divided into supersonic and subsonic heat release zones. The reaction in the channel was mainly diffusion combustion， and gradually transited to premixed combustion along with the mixing process. With the increase of the rocket mass flow rate， the temperature and the reaction distance increases， however， the mixing efficiency decreases.

Key words: Combined cycle engine;Ejector mode;Combustion;Air entrainment;Mixing;Premixed combustion

石磊，赵国军，杨一言，秦飞，魏祥庚，何国强. 中心支板式RBCC发动机引射模态流动与燃烧研究[J]. 推进技术, 2020, 41(10): 2292-2301.

SHI Lei, ZHAO Guo-jun, YANG Yi-yan, QIN Fei, WEI Xiang-geng, HE Guo-qiang. Flow and Combustion of Central-Strut Based RBCC Engine in Ejector Mode[J]. Journal of Propulsion Technology, 2020, 41(10): 2292-2301.

参考文献

[1] 王亚军，何国强，秦飞，等，火箭冲压组合动力研究进展［J］. 宇航学报， 2019， 40（10）： 1125-1133.
[2] Lei Shi， Guojun Zhao， Yiyan Yang， et al. Research Progress on Ejector Mode of Rocket-Based Combined-Cycle Engines［J］. Progress in Aerospace Sciences， 2019， 107： 30-62.
[3] 黄国庆. 火箭基组合循环发动机引射模态性能研究［D］. 长沙：国防科学技术大学， 2010.
[4] 安佳宁. RBCC（火箭基组合循环）引射模态研究［D］. 长沙：国防科学技术大学， 2011.
[5] 鲍文，秦江，唐井峰，等. 吸气式高超声速推进热力循环分析［M］. 北京：科学出版社， 2013.
[6] Yang Q， Shi W， Chang J， et al. Maximum Thrust for the Rocket-Ejector Mode of the Hydrogen Fueled Rocket-Based Combined Cycle Engine［J］. International Journal of Hydrogen Energy， 2015， 40： 3771-3776.
[7] 林其. 火箭基组合循环发动机（RBCC）引射模态的准一维理论分析［D］. 绵阳：中国空气动力研究与发展中心， 2009.
[8] 陈立红，高子阳，张新宇，等. 模拟火箭引射混合特性的实验研究［J］. 力学与实践， 2002， 24（5）： 22-24.
[9] 王国辉，蔡体敏，何国强，等. 火箭基组合循环发动机引射模态流动分析［J］. 推进技术2002， 23（4）： 298-302.
[10] Kanda T， Kato K， Tani K， et al. Experimental Study of a Combined-Cycle Engine Combustor in Ejector-Jet Mode［R］. AIAA 2006-223.
[11] Han S， Tomes J， Lane J. Numerical Study of PSU-RBCC Ejector Mode Operation［R］. AIAA 2003-5230.
[12] Tani K， Kanda T， Tokutome S. Aerodynamic Characteristics of the Combined Cycle Engine in an Ejector Jet Mode［R］. AIAA 2005-1210.
[13] Tomioka S， Takegoshi M， Kudo K， et al. Performance of a Rocket-Ramjet Combined Cycle Engine Model in Ejector Mode Operation［R］. AIAA 2008-2618.
[14] Lineberry D， Landrum B. Effects of Multiple Nozzles on Asymmetric Ejector Performance［R］. AIAA 2005-4283.
[15] Shi L， He G Q， Liu P J， et al. A Rocket-Based-Combined-Cycle Engine Demonstrating Comprehensive Component Compatibility and Effective Mode Transition［J］. Acta Astronautica， 2016， 128： 350-362.
[16] Wang T S. Thermophysics Characteristics of Kerosene Combustion［R］. AIAA 2000-2511.
[17] Shi L， Liu X W， He G Q， et al. Numerical Analysis of Flow Features and Operational Characteristics of a Rocket-Based Combined-Cycle Inlet in Ejector Mode［J］. Acta Astronautica， 2016， 127： 182-196.
[18] Zhang Z Z， Liu P J， Qin F， et al. Numerical and Experimental Investigations on the Influence of Inlet Contraction Ratio for a Rocket-Based Combined Cycle Engine［J］. Acta Astronautica， 2018， 149： 1-10.
[19] Ye J， Pan H， Qin F， et al. Simulation of Kerosene Combustion Sustaining with Cavities in a Strut-Based RBCC Engine［R］. AIAA 2015-3837.
[20] Jinying Ye， Hongliang Pan， Fei Qin， et al. Investigation of RBCC Performance Improvements Based on a Variable Geometry Ramjet Combustor［J］. Acta Astronautica， 2018， 151： 874-885.
[21] 叶进颖. RBCC变结构燃烧室工作特性研究［D］. 西安：西北工业大学， 2018.
[22] 薛瑞. RBCC隔离段气动特性及与燃烧室相互作用研究［D］. 西安：西北工业大学， 2016.
[23] 林彬彬. RBCC引射模态主火箭与全流道匹配技术研究［D］. 西安：西北工业大学， 2017.
[24] 曹东刚. 受限空间内超声速反应混合层生长及释热特性研究［D］. 西安：西北工业大学， 2018.

中心支板式RBCC发动机引射模态流动与燃烧研究

Flow and Combustion of Central-Strut Based RBCC Engine in Ejector Mode

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