固体火箭发动机涡声耦合不稳定燃烧研究进展

As one of the key excitation mechanisms inducing combustion instability in solid rocket motors(SRMs), vortex-acoustic coupling has long been a critical bottleneck restricting the design and development of solid rocket motors. From the perspective of theoretical development, the evolution of vortex-acoustic coupling research is systematically traced, highlighting its migration from fundamental fluid dynamics to the field of combustion instability in solid rocket motors. From the perspective of engineering application, typical cases of vortex-acoustic coupling failures in foreign representative SRM programs are summarized. Based on existing theoretical systems, the core factors inducing vortex-acoustic instability are classified into five categories: geometric configurations of submerged nozzles and cavities, flow characteristics of combustion gases, geometric and physical parameters of structures such as baffles and corners, two-phase flow characteristics in the combustion chamber, and motor length-to-diameter ratio. Through the analysis of domestic and international engineering cases and research achievements, three mainstream technical approaches for suppressing vortex-acoustic oscillations are summarized, namely noise reduction(optimizing cavity volume and location), vortex regulation(modifying propellant grain configurations), and flow disturbance(installing mechanical suppression devices), which can provide technical references for engineering designers. Finally, future research directions are outlined, including vortex-acoustic energy coupling modeling, nonlinear amplification mechanisms of vortex-acoustic oscillations, construction of dedicated vortex-acoustic test platforms, and refined vibration suppression technologies, thus clarifying the direction for further in-depth investigation.