固冲发动机补燃室流场条件下硼燃烧试验研究  

Experimental Investigation of Boron Combustion in Flow Field Conditions in Secondary Chamber of Ducted Rocket

作　　者：刘道平[1] 夏智勋[1] 黄利亚[2] 胡建新[2] 

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙410073 [2]国防科技大学航天科学与工程学院,湖南长沙410073

出　　处：《含能材料》2015年第3期248-252,共5页Chinese Journal of Energetic Materials

基　　金：国家自然科学基金资助(51276194)

摘　　要：建立了一套固冲发动机地面模拟试验系统,用于研究补燃室流场条件下硼的燃烧,该试验系统用乙醇与氧气反应加热硼颗粒,并与空气二次燃烧的方式,模拟含硼固冲发动机的工作过程,其一次燃烧产物主要为H2、CO和硼颗粒,补燃室总温、静温值为1300-1400K,总压、静压值为0.4-0.5MPa,马赫数值为0.35左右,与真实固冲发动机相关参数值相符合。基于此试验系统,采集了燃气发生器、补燃室进气口、掺混区、燃烧区和喷管等位置的凝相燃烧产物。扫描电镜（SEM）、X射线衍射（XRD）和X射线能谱（EDS）分析结果表明,硼在反应过程中呈颗粒状,整体形貌变化不太明显,大部分的硼在补燃室中完成反应,燃烧区硼的反应量最大,靠近喷管区域次之,掺混区域最少。Boron based ducted rocket experimental system for ground simulation was established to study the boron combustion.Through heating the boron in a primary chamber by the combustion gas of the ethanol and oxygen,and using air react with boron in the secondary chamber,the working process under the condition of the flow field was simulated,and the similar condition for the real ducted rocket was obtained as following：the compositions of primary products are H2,CO and boron particles,and in the secondary chamber,the total and static temperatures 1300-1400 K,total and static pressures 0.4-0.5 MPa and Mach number about 0.35.With the experimental system,the condensed products at different axial locations including the primary chamber,secondary chamber inlet,mixture region,combustion region,nozzle,were collected and analyzed by the Scanning Electron Microscope,X-ray diffraction and the energy dispersive X-ray spectroscopy.Results show that boron particles are grain during the reaction and its morphology changes a little.The boron is combusted mainly in the secondary chamber,and most in the combustion region,less in the region before the nozzle,and the lest in the mixture region.

关 键 词：固冲发动机 补燃室 硼 试验研究 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]