气体中心型气液同轴离心式喷嘴在液体火箭发动机中得到广泛应用，例如我国新一代大推力液体火箭发动机YF-100、YF-115等都采用了此类型的喷嘴，其雾化性能对火箭发动机的燃烧效率、稳定性和相容性起决定性作用。目前，气体中心型离心式喷嘴液膜表面波演化过程、雾化过程、喷雾自激振荡诱发机理的研究还存在不足。本项目拟针对气体中心型离心式喷嘴的液膜破碎过程、雾化特性和自激振荡机理开展研究，分析气相流场中涡脱落、涡破碎和涡核进动等气相非定常流场运动对液膜纵向和周向表面波演化过程的影响，进一步研究喷嘴内部声腔、声学激励和扰流装置作用下的液膜表面波演化过程、液膜破碎机制和喷嘴雾化特性，总结有/无扰动情况下气体中心型离心式喷嘴的自激振荡诱发机理。总结获得用于增强气体中心型离心式喷嘴雾化特性的有效方法和抑制喷嘴自激振荡的实用技术。研究结果可用于指导液体火箭发动机喷嘴的工程设计，加深对发动机不稳定燃烧的全面认识。

Gas-centered swirl coaxial (GCSC) injectors are widely employed in Liquid Rocket Engine (LRE). For example, the advanced high-propulsion LRE in China, YF-100 and YF-115, utilized GCSC injectors. These injectors affect the combustion efficiency, stability and compatibility in LRE. At present, research on the atomization process and the mechanism of spray self-pulsation of a GCSC injector is still insufficient. This project would investigate the growth of tangential and axial surface waves on the liquid film, the atomization characteristics and self-pulsation mechanisms of GCSC injector. Details about the effects of vortex breakup, vortex shedding and processing vortex core on surface wave of the liquid film would be studied. Additionally, effects of acoustic cavity, acoustic excitation and other disturbance on liquid film and atomization characteristics would be analyzed. Mechanisms of spray self-pulsation of a GCSC injector would then be obtained. Methods aiming at obtaining a better performance of spray atomization or avoiding the spray self-pulsation would be tested and developed. Results from the fundamental study in this project can be used to guide the GCSC injector design in a LRE and also deepen the understanding of combustion instability in LRE.