空天防御2024，Vol.7Issue(3)：54-63,10.
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
Study on the Influence of Combustor Configuration on Combustion Characteristics of Solid Rocket Scramjet
摘要
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.关键词
固体火箭超燃冲压发动机/燃烧室/燃烧特性/硼颗粒Key words
solid rocket scramjet/combustor/combustion characteristics/boron particle分类
航空航天引用本文复制引用
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):54-63,10.基金项目
国家自然科学基金(12272409) （12272409）
国家自然科学基金创新研究群体项目(T2221002) （T2221002）
湖南省研究生科研创新项目(QL20230015) （QL20230015）
