液体火箭发动机燃烧不稳定机理研究综述OA
Review of Research on Mechanisms of Combustion Instability in Liquid Rocket Engines
燃烧不稳定是发展液体火箭发动机最大的技术难题之一.针对液体火箭发动机燃烧不稳定产生机理,文章从火焰-声波、火焰-涡、喷注耦合、雾化、蒸发控制的燃烧不稳定5个方面开展综述,系统梳理了不同诱发机制的研究进展,归纳总结了面临的挑战和后续发展方向,重点强调了光学诊断技术和高保真数值模拟方法对驱动机理研究的重要意义,为燃烧不稳定的机理研究和液体火箭发动机设计提供参考依据.
Combustion instability is the most significant technical challenge in developing liquid rocket engines.A com-prehensive review of the generation mechanisms of combustion instability in liquid rocket engines is presented,includ-ing flame-acoustic,flame-vortex,injection-coupled,atomization-controlled,and evaporation-controlled combustion in-stability.The research progress on different inducing mechanisms is systematically organized,and the challenges faced and future development directions are summanrized.The significance of optical diagnostic techniques and high-precision numerical simulation methods in studying driving mechanisms is emphatically emphasized.This review aims to provide a reference for the study of combustion instability mechanisms and the design of liquid rocket engines.
曹炜;郭康康;仝毅恒;苏凌宇;黄卫东;聂万胜
航天工程大学宇航科学与技术系,北京 101416航天工程大学宇航科学与技术系,北京 101416航天工程大学宇航科学与技术系,北京 101416航天工程大学宇航科学与技术系,北京 101416航天工程大学宇航科学与技术系,北京 101416航天工程大学宇航科学与技术系,北京 101416
航空航天
液体火箭发动机燃烧不稳定机理热声耦合涡脱落喷注耦合雾化控制蒸发控制
liquid rocket enginecombustion instability mechanismthermoacoustic couplingvortex sheddinginjection-coupledatomization controlevaporation control
《海军航空大学学报》 2026 (4)
595-616,632,23
国家自然科学基金(12372254)
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