Abstract：To improve the combustion performance of solid rocket scramjet and understand the effect of combustor
design parameters on combustion mode and performance, this study has analyzed the impact of the minimum
geometric throat of combustor and the distance between the front edge of cavity and fuel injector port on the flow
and gas-solid two-phase combustion characteristics in the combustor using numerical simulation. The results show
that the minimum geometric throat of the combustor affects the position of the thermal throat by changing the
degree of obstruction in the combustor. With the increasing distance between the front edge of the cavity and the
fuel injector port, the resulting low-speed zone presents a stronger blocking effect on the air flow, thus increasing
the retention time of the particulate phase fuel and improving the combustion efficiency. The combustion efficiency
of particulate phase fuel is the key factor that dominates the overall combustion efficiency, and affects the
improvement of the combustor performance and the modification of combustion mode.
赵李北, 夏智勋, 马立坤, 陈斌斌, 冯运超, 杨鹏年, 李潮隆, 刘延东. 固体火箭超燃冲压发动机燃烧室构型对燃烧特性影响研究[J]. 空天防御, 2024, 7(3): 54-63.
ZHAO Libei, XIA Zhixun, MA Likun, CHEN Binbin, FENG Yunchao, YANG Pengnian, LI Chaolong, LIU Yandong. Study on the Influence of Combustor Configuration on
Combustion Characteristics of Solid
Rocket Scramjet. Air & Space Defense, 2024, 7(3): 54-63.
