关于超声速燃烧与高超动力

姜宗林

doi:10.6052/1000-0992-21-008

关于超声速燃烧与高超动力

doi: 10.6052/1000-0992-21-008

姜宗林^*, ,

中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190

基金项目:

国家自然科学基金 (11727901, 11532014, 12072353) 资助项目.

详细信息

作者简介:
*E-mail: zljiang@imech.ac.cn
姜宗林, 中国科学院力学研究所研究员, 所学术委员会常务副主任. 毕业于北京大学力学系, 获博士学位. 一直从事激波计算方法、激波与爆轰物理、高温与高超声速气体动力学领域的研究工作, 在激波捕捉频散控制耗散格式、爆轰统一框架理论、爆轰驱动高焓激波风洞和斜爆轰冲压发动机的理论与技术方面都取得重要进展, 曾获美国航空航天(AIAA)地面试验奖、国家技术发明、中科院杰出科技成就奖、中国力学科技进步奖.

通讯作者:
姜宗林

中图分类号: O35
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出版历程
- 收稿日期: 2021-02-22
- 刊出日期: 2021-03-25

On supersonic combustion and hypersonic propulsion

JIANG Zonglin^{*
, ,}

State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

More Information

Corresponding author: JIANG Zonglin

摘要

摘要: 先进发动机是航空工业的核心技术, 而吸气式高超声速发动机一直是宇航飞行技术研发的首位难题. 发动机的性能依赖于其能量转换模式和燃烧组织方法, 相关理论研究具有基础性和启发性意义. 论文首先讨论了超声速燃烧, 它一直是超燃冲压发动机技术的理论基础. 然后综述了相关研究进展, 提出了吸气式高超声速冲压推进技术的3个临界条件, 或者称为临界参数. 第一临界条件针对超声速气体流动中燃烧发生部位的亚声速或超声速状态的判定问题, 由此可以揭示上行激波的产生机制, 也能够作为燃烧后气体流动状态的判定条件; 第二临界参数定义了在当量比燃烧条件下吸气式高超声速冲压发动机的稳定运行马赫数, 是发动机设计需要考虑的必要条件. 第三临界参数给出了对应CJ斜爆轰的楔面角度, 其物理基础是爆轰临界起爆状态. 最后总结了驻定斜爆轰冲压发动机的实验研究进展, 论述了作为未来高超声速飞行动力的可行性.
- 超燃冲压发动机 /
- 临界参数 /
- 超声速燃烧 /
- 驻定斜爆轰冲压发动机 /
- 斜爆轰
Abstract: The advanced engine has been the core technology of the aviation industry for several decades. The air-breathing hypersonic propulsion is the top problem for future aerospace flight. The engine's performance depends on its energy conversion method and combustion mode, and its relevant theory is of fundamental and revealing significance. In this paper, the supersonic combustion is discussed first since it is the theoretical basis for the research and development of scramjet engines. Then, by reviewing related research progresses, three criteria of the air-breathing hypersonic ramjet propulsion are established. The first one can be used to determine the local subsonic or supersonic flow states of combustion products in supersonic reacting gas flows, revealing the mechanism of the upstream-traveling shock wave. The second one defines the critical Mach number for hypersonic ramjet operation for all the combustion modes, and is a necessary condition that needs to be considered in the engine design under the equivalent ratio combustion. The last one gives a critical wedge angle corresponding to the CJ oblique detonation, and its physical basis is the critical initiation state of detonation. Finally, the experimental research progress on the stationary oblique detonation ramjet (Sodramjet) engine is summarized, and its feasibility as a hypersonic engine for future aerospace flight is demonstrated.
- scramjet /
- criteria /
- supersonic combustion /
- oblique detonation /
- sodramjet.

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参考文献(23)

[1]	顾诵芬, 史超礼. 1988. 世界航空发展史. 河南: 河南科学技术出版社.
[2]	姜宗林. 2009. 关于吸气式高超声速推进技术研究的思考. 力学进展, 39(4):398-406.
[3]	姜宗林等. 2020. 气体爆轰物理及其统一框架理论. 北京: 科学出版社.
[4]	刘大响, 程荣辉. 2002. 世界航空动力技术的现状及发展动向. 北京航空航天大学学报, 28(5):490-496.
[5]	Anderson J D. 1989. Hypersonic and High Temperature Gas Dynamics. New York: McGraw-Hill Book Company.
[6]	Billig F S. 1993. Research on supersonic combustion. Journal of Propulsion & Power, 9(4):499-514.
[7]	Choi J Y, Ma F, Yang V. 2005. Combustion oscillations in a scramjet engine combustor with transverse fuel injection. Proc Combust Inst. 30:2851-2858.
[8]	Heiser W H, Pratt D T. 1994. Hypersonic Air-breathing Propulsion. Reston. AIAA Ins.
[9]	Jiang Z, Yu H. 2017. Theories and technologies for duplicating hypersonic flight conditions for ground testing. National Science Review, 4(3):290-296.
[10]	Jiang Z, Liu Y, Wang C, Luo C. 2019. Shock waves generated from the combustion in supersonic flows//32nd International Symposium on Shock Waves. Singapore, July 14-19.
[11]	Jiang Z, Li J, Hu Z, Liu Y, Yu H. 2020. On theory and methods for advanced detonation-driven hypervelocity shock tunnels. National Science Review, 7(7):1198-1207.
[12]	Jiang Z, Zhang Z, Liu Y, Wang C, Luo C. 2021. The criteria for hypersonic airbreathing propulsion and its experimental verification. Chinese Journal of Aeronautics, 34(3):94-104.
[13]	Lin K C, Ma F, Yang V. 2010. Acoustic characterization of an ethylene-fueled scramjet combustor with a cavity flame-holder. J Propul Power, 6(26):1161-1169.
[14]	Oppenheim A K. 2006. Dynamics of Combustion Systems. New York: Springer.
[15]	Peedles C. 2007. Road to Mach 10: Lessons Learned from the X-43A Flight Research Program. Reston. AIAA Ins.
[16]	Stillwell W H. 1965. X-15 Research Results: With a Selected Bibliography. Washington DC: National Aeronautics and Space Administration.
[17]	Teng H, Jiang Z. 2012. On the transition pattern of the oblique detonation structure. Journal of Fluid Mechanics, 713:659-669.
[18]	Teng H, Ng H D, Li K, Luo C, Jiang Z. 2015. Evolution of cellular structures on oblique detonation surfaces. Combustion and Flame, 162:470-477.
[19]	Viguier C, Silva L, Desbordes D, et al. 1996. Onset of oblique detonation waves: Comparison between experimental and numerical results for hydrogen-air mixtures. Symposium (International) on Combustion, 26(2):3023-3031.
[20]	Wang C, Han Z, Situ M. 2006. Investigation of high speed combustible gas ignited by a hot gas jet produced in the shock tube. Shock Waves, 15(2):129-135.
[21]	Yang P, Teng H, Jiang Z, Ng H. 2018. Effects of inflow Mach number on oblique detonation initiation with a two-step induction-reaction kinetic model. Combustion and Flame, 193:246-256.
[22]	Yuan S X. 1999. On supersonic combustion. Science China Mathematics, 42(2):171-179.
[23]	Zucrow M J, Hoffman J D. 1976. Gas Dynamics. John Wiley and Sons. Ins.