Metal/N_2O粉末火箭发动机实验研究  

Experimental research on metal/N_2O powder rocket engine

作　　者：邓哲[1] 胡春波[1] 卢子元 胡松启[1] 张研[1] 徐义华[2] 

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072 [2]南昌航空大学飞行工程学院,南昌330063

出　　处：《固体火箭技术》2015年第2期220-224,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(51266013);国防基础科研基金(B0320132006);西北工业大学基础研究基金(JC20110205)

摘　　要：采用气压驱动供粉方式,开展了Metal/N2O火箭发动机点火实验。通过分析活塞位移及燃烧室压强振荡,研究了两相流动特性。根据液滴燃烧模型,分析了燃烧室压强、颗粒滞留时间、氧燃比等因素对发动机燃烧效率的影响。通过以上研究,验证了此种发动机的优良性能。结果表明,输送管路中固相浓度脉动幅度在颗粒粒径40μm、两相流空隙率97%、氮气流动速度27 m/s情况下小于±0.36%;Mg/N2O实验平均特征速度效率在燃烧室压强0.5 MPa情况下高达96.4%,Al/N2O实验在燃烧室0.91 MPa情况下燃烧效率达到88.5%;提高燃烧室压强、颗粒滞留时间,可提高燃烧效率,但氧燃比对燃烧效率影响较为复杂。Hot fire tests of metal/N2O rocket engine were carried out,using pneumatic driving powder feeding device.The two-phase flow characteristics were investigated through analyzing piston displacement and combustion pressure oscillation.According to droplet combustion model,the influence of factors such as combustion chamber pressure,particle residence time and O/F ratio were analyzed.The study verifies good performance of the engine. The results show that the concentration pulsating amplitude of solid phase in pipeline is less than ±0.36% when two-phase flow void ratio is 97% and flow velocity is 27 m/s.The average characteristic velosity efficiency of Mg/N2 O tests are about 96.4% at 0.5 MPa combustion chamber pressure,and reaches 88.5% of Al/N2 O tests at 0.91 MPa. Increasing combustion chamber pressure and particle residence time can improve combustion efficiency,but the effect of O/F ratio on combustion efficiency is relatively complex.

关 键 词：金属粉末 气固两相流 燃烧振荡 燃烧效率 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]