摘要
通过CFD方法建立了一个耦合化学反应的多孔介质二维拟均相反应器模型,利用此模型研究了耗氧型惰化系统不同工况下反应器的操作范围及工作性能。以RP-3燃油为研究对象,采用Fluent 17.0软件的多孔介质单温度模型,通过UDS(user defined scalar)添加固相能量方程,通过源项形式添加化学反应热到固相能能量方程。研究了不同表观气速、RP-3摩尔分数时反应器在不飞温状况下的操作范围,引入耗氧速率作为反应器对惰化系统影响的评价指标,讨论了进口气体温度对反应器操作范围及性能的影响。结果显示:反应器有一定的操作范围,增加反应器进口气体温度会缩小可操作范围;随着进口表观气速增加耗氧速率趋于不变;RP-3摩尔分数、进口气体温度增加都会大幅提升耗氧速率。因此在未来设计耗氧型惰化反应器时应充分考虑这些因素。
A two-dimensional pseudo-homogeneous reactor model of porous media coupled with chemical reaction was established by CFD method to research the operating range of the reactor in the oxygen consumption based inerting system as well as the impact on the reactor performance under different working conditions.The single-temperature model of porous media in Fluent 17.0 software was adopted,and the solid phase energy equation was added through UDS(user defined scalar).RP-3 fuel was taken as the object,and the chemical reaction heat was added to the solid phase energy equation in the form of source term.The operating range of the reactor was analyzed under the condition of different superficial gas velocity and different RP-3 mole fraction without temperature runaway,the indicator of oxygen consumption rate was introduced to evaluate the influence of the reactor on the inerting system,and the influence of the inlet gas temperature on the operating range and reactor performance was discussed.Results showed that the reactor had a certain operating range,and increasing the inlet gas temperature would reduce the operating range;the oxygen consumption rate tended to be constant with the increase of inlet gas velocity;the oxygen consumption rate would be greatly increased by RP-3 mole fraction and the temperature rise of the inlet gas.Therefore,these factors should be fully considered in the future design of oxygen consumption based inerting reactor.
作者
冯诗愚
谢辉辉
彭孝天
任童
潘俊
王洋洋
FENG Shiyu;XIE Huihui;PENG Xiaotian;REN Tong;PAN Jun;WANG Yangyang(Key Laboratory of Aircraft Environmental Control and Life Support Industry and Information Technology,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration,Nanjing Engineering Institute of Aircraft Systems,Aviation Industry Corporation of China Limited,Nanjing 211106,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第2期318-324,共7页
Journal of Aerospace Power
基金
国家自然科学基金委员会-中国民用航空局民航联合研究基金(U1933121)
中央高校基本科研业务费专项资金
江苏省科研与实践创新计划(KYCX19_0198)
江苏高校优势学科建设工程.