喷注位置对多组分燃料超燃冲压发动机燃烧的影响
Influence of injection position on combustion of multi-component fuel scramjet
滑远帆 1李世鹏 2王宁飞 2于文浩 3马源辰2
作者信息
- 1. 北京理工大学宇航学院,北京 100081;中国航天科技集团有限公司北京航天动力研究所,北京 100076
- 2. 北京理工大学宇航学院,北京 100081
- 3. 沈阳航空航天大学航空宇航学院,沈阳 110136
- 折叠
摘要
为研究含铝高能量密度碳氢燃料在超燃冲压发动机中的燃烧组织细节,使用离散相模型(DPM)和简化反应机理对不同燃料喷注位置下燃烧流动过程进行了数值模拟.结果表明:使用七喷注器从上壁面进行燃料喷注时,出口截面处温度场形成了以近上壁面轴线为中心低温-升至最高温-降至较低温度的分布特征,氧浓度在中心处的含量也较低,这都将影响燃烧反应的进程.在研究工况下随着喷注器与燃烧室入口距离增大,燃料比冲呈先增大后减小的变化趋势,在研究工况中实现燃料最大比冲11 092 m/s,可以通过改变燃料从上壁面喷入燃烧室的喷注位置和优化喷注器布局等提升燃烧室性能,优化后最大比冲提升了12.68％.
Abstract
In order to investigate the details of the combustion organization of aluminum-containing high-energy-density hydrocarbon fuels in scramjet engine,a discrete phase model(DPM)and simplified reaction mechanism were used to numerically simulate the combustion flow process at different fuel injection positions.The results showed that when the seven injectors were used to inject fuel from the upper wall,the exit section formed a temperature distribution near the center of the upper wall from inside to outside,namely,relatively low temperature-warming-up to the highest temperature-cooling down.The lower oxygen concentration of the upper wall near the center area affected the progress of the reaction.Under the research conditions,as the distance between the injector and the inlet of the combustion chamber increased,the fuel specific impulse first increased and then decreased.In the research condition,the maximum specific impulse of fuel was 11 092 m/s.The performance of the combustion chamber can be improved by changing the injection position of the fuel injected into the combustion chamber from the upper wall and optimizing the injector layout.After optimization,the maximum specific impulse increased by 12.68％.
关键词
多组分燃料/超燃冲压发动机/喷注位置/燃烧性能/喷注布局优化Key words
multi-component fuel/scramjet/injection position/combustion performance/spray layout optimization引用本文复制引用
出版年
2024
NETL
NSTL
万方数据