Abstract A review of fundamental research in combustion stabilization for hypersonic airbreathing propulsion is presented. Combustion in high-speed airbreathing propulsion systems demands stable flame distribution and chemical reaction to provide reliable thrust over a wide flight envelope. Various methods have been developed to stabilize combustion depending on the hypersonic regime. For low hypersonic conditions, combustion occurs mainly in the diffusive mode in which the gas/liquid fuels are injected into supersonic freestreams for simultaneous fuel-air mixing and chemical reaction. Flame stability is generally enhanced by improved mixing, physical flameholding, and external energy addition. In higher hypersonic conditions, partially/fully premixed combustion relying on shock induced stabilization becomes more dominant. In such cases, flame stabilization can be achieved through alternative means such as radical generation and standing oblique detonation waves. The review outlines both experimental and numerical research progress made towards combustion stabilization over the entire hypersonic regime, and intended to lay the groundwork for further studies which can provide optimized design guidelines for the next generation of high-speed airbreathing propulsion systems.

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高超声速吸气式推进的燃烧稳定性综述

摘要 综述了高超声速吸气式推进燃烧稳定的基础研究。高速吸气式推进系统中的燃烧需要稳定的火焰分布和化学反应，以在较宽的飞行包线内提供可靠的推力。已经开发了各种方法来根据高超声速状态稳定燃烧。对于低超音速条件，燃烧主要以扩散模式发生，其中气体/液体燃料被注入超音速自由流中，同时进行燃料-空气混合和化学反应。火焰稳定性通常通过改进混合、物理火焰稳定和外部能量添加来增强。在更高的高超音速条件下，依赖冲击引起的稳定的部分/完全预混燃烧变得更加重要。在这种情况下，火焰稳定可以通过替代方法实现，例如自由基产生和驻留斜爆轰波。该综述概述了在整个高超声速状态下在燃烧稳定方面取得的实验和数值研究进展，旨在为进一步研究奠定基础，为下一代高速吸气推进系统提供优化设计指南。