Abstract: Ground direct-connected experiments and numerical simulations were carried out to obtain the influence factors of the combustion performance of the solid rocket scramjet operating in cruise mode at flight Mach number 5.5. The effects of the injection mode of the fuel-rich gas， stages of the turbulence device and the expansion ratio of combustor on the performance of combustor were studied by numerical method. A combustor configuration with a vertical injection mode was found to be with a high combustion efficiency （≥90%）. The results show that： （1） The vertical injection mode could enhance the mixing process of fuel-rich gas and air， and the combustion efficiency of particle phase was 25% higher than that of the central-strut with dual-rockets configuration. （2） The effects of different number of turbulence device stages on engine performance were compared. As thermal protection of turbulence devices and the complexity of engine structure were considered， the combustor with double stages turbulence devices was considered to be the best choice. The combustion efficiency of the particle phase in this combustor was 26% higher than that of the combustor with a single-stage turbulence device. （3） The effects of different combustor expansion ratios on engine performance were compared. The combustion efficiency of the particle phase was 95% when the expansion ratio of the combustor was 1.6. In conclusion， a combustor with a vertical injection mode， double-staged turbulence device and a combustor expansion ratio of 1.6 were optimized with high combustion efficiency.

Key words: Solid rocket;Scramjet engine;Combustion performance;Turbulence device;Particle phase

摘要： 为了获得以飞行马赫数5.5巡航工作的固体火箭超燃冲压发动机燃烧性能影响因素，开展了地面直连试验和数值模拟研究。利用数值手段研究了固体燃气喷注方式、扰流装置的形式以及燃烧室扩张比等因素对燃烧室性能的影响规律，获得了高燃烧效率 （≥90%） 的壁面垂直喷注式发动机燃烧室构型。研究表明：（1） 壁面垂直喷注方式能增强富燃燃气与空气的掺混效果，颗粒相的燃烧效率较中心支板式双火箭燃烧室构型提高了25%。（2） 对比不同级数的扰流装置对发动机性能影响，同时考虑扰流装置热防护问题和发动机结构复杂程度，双级扰流装置的扰流形式增强效果较优，颗粒相的燃烧效率较单级扰流装置的燃烧室构型方案提高了26%。（3） 对比不同燃烧室扩张比对发动机性能影响，扩张比为1.6的燃烧室构型方案颗粒相的燃烧效率为95%。综上所述，通过优化得到了壁面垂直喷注方式、双级扰流装置以及燃烧室扩张比为1.6的高燃烧效率的发动机燃烧室构型。

关键词: 固体火箭;超燃冲压发动机;燃烧性能;扰流装置;颗粒相