超声速燃烧室凹腔构型优化研究进展-流动控制与热管理专栏

doi:10.7527/S1000-6893.2026.33007

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超声速燃烧室凹腔构型优化研究进展-流动控制与热管理专栏

周子旋¹,张林²,³,孙明波³,杨伟奇⁴,乔竑玮³,陈玉俏⁵,张桐⁶

1. 国防科技大学先进推进技术实验室
2.
3. 国防科技大学
4. 国防科技大学空天科学学院
5. 中国人民解放军国防科技大学空天科学学院临近空间技术研究所
6. 国防科技大学空天科学学院先进推进技术实验室

收稿日期:2025-10-31 修回日期:2026-03-09 出版日期:2026-03-16 发布日期:2026-03-16
通讯作者: 张林
基金资助:
国家自然科学基金;湖南省科技创新计划

Research Progress on Cavity Configuration Optimization for Supersonic Combustors

Received:2025-10-31 Revised:2026-03-09 Online:2026-03-16 Published:2026-03-16

摘要/Abstract

摘要： 对于吸气式高超声速飞行器，燃料与超声速气流的快速充分混合、高效燃烧与火焰稳定是其动力系统即超燃冲压发动机设计的核心挑战。凹腔作为最常用的超燃冲压发动机燃烧室火焰稳定装置之一，其构型对燃料的混合燃烧过程乃至燃烧室性能具有深刻影响。本文系统综述了凹腔构型对超声速燃烧室中流动燃烧过程及其性能影响的研究进展。首先对超声速凹腔构型特点、燃烧流场特征结构及物理效果进行了简介。其次，总结分析了凹腔长度、深度、长深比、后缘倾角、前缘倾角等基本构型参数对凹腔回流区结构、燃料驻留时间及火焰稳定性等流动燃烧特性的影响规律。再次，从回流区/涡结构拓展、激波/膨胀波系重构、剪切层调控三方面促进混合燃烧的物理机制出发，对二维凹腔构型优化工作进行系统阐述；进一步聚焦三维凹腔优化与创新设计，探讨了流向涡增强、横向质量交换等优化方法及相关研究进展。最后，结合当前研究现状与技术瓶颈，对凹腔火焰稳定器构型优化与设计提出了建议。

关键词: 超燃冲压发动机, 凹腔构型, 燃烧室性能, 混合增强, 火焰稳定

Abstract: In air-breathing hypersonic vehicles, scramjet propulsion systems face core challenges such as fast and adequate fuel-supersonic airflow mixing, effective combustion, and robust flame stabilization. As one of the most widely used flame stabilization devices in scramjet combustors, the cavity shows a profound influence on the fuel mixing and combustion process, as well as the combustor performance. This paper systematically reviews research progress on the effects of cavity configurations on flow characteristics and combustor performance in supersonic combustors. First, a concise overview of the supersonic cavity is introduced, including the basic configurations, the typical flow structures, and mixing and combustion enhancement in both non-reactive and reactive flows. Second, the influence of fundamental cavity configuration parameters, including cavity length, depth, length-to-depth ratio, rear-wall inclination angle, and front-wall inclination angle, on flow and combustion characteristics is summarized and analyzed. Third, the optimization of two-dimensional cavity configurations is systematically elaborated on the basis of three physical mechanisms: extension of recirculation zones/vortical structures; reconstruction of shock/expansion wave systems; and modulation of shear layer dynamics. Furthermore, three-dimensional cavity optimization is discussed, with a focus on the streamwise vortex enhancement and lateral mass exchange. Finally, recommendations are proposed for the configuration optimization and design of cavity flameholders, taking into account the current research status and technical bottlenecks.

Key words: scramjet, supersonic combustor, cavity configuration optimization, combustor performance, flame stability

中图分类号:

周子旋张林孙明波杨伟奇乔竑玮陈玉俏张桐. 超声速燃烧室凹腔构型优化研究进展-流动控制与热管理专栏[J]. 航空学报, doi: 10.7527/S1000-6893.2026.33007.

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超声速燃烧室凹腔构型优化研究进展-流动控制与热管理专栏

Research Progress on Cavity Configuration Optimization for Supersonic Combustors

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