CAJ | 학술논문

为实现固冲发动机二次燃烧模型验证，结合固冲发动机工作条件，设计了一种带透明观察窗燃烧实验装置；营造了简单的燃烧环境，实现了燃烧过程掺混作用的弱化；借助高速摄像进行了以空气速度作为单一变量的含硼富燃燃气燃烧可视化测量，获得了火焰形态结构；采用高速数据采集，获得了燃烧室压力；将实验数据与数值模拟结果进行了对比和分析。结果表明，燃气与空气速度相近时，火焰呈锥角结构，硼粒子的点火距离较长；燃气与空气速度差较小时，同一位置燃烧室压力较大；燃气与空气速度近似程度决定火焰的形态；数值模拟结果与实验结果基本吻合。
위실현고충발동궤이차연소모형험증，결합고충발동궤공작조건，설계료일충대투명관찰창연소실험장치；영조료간단적연소배경，실현료연소과정참혼작용적약화；차조고속섭상진행료이공기속도작위단일변량적함붕부연연기연소가시화측량，획득료화염형태결구；채용고속수거채집，획득료연소실압력；장실험수거여수치모의결과진행료대비화분석。결과표명，연기여공기속도상근시，화염정추각결구，붕입자적점화거리교장；연기여공기속도차교소시，동일위치연소실압력교대；연기여공기속도근사정도결정화염적형태；수치모의결과여실험결과기본문합。
A test facility,which has transparent observation windows,was designed to solve the verification of secondary com?bustion models according to the working conditions of solid rocket?ramjet motor(SRRM).This facility was made to shorten the effect of mixing and form simple combustion environment.The combustion phenomena of fuel?rich gas containing boron particles,which was based on the single variable of air inlet velocity,were studied with the help of high?speed photographer and data acquisition. The shape of fire and pressure of combustion chamber were observed and numerical simulation was then compared with the experiment data.The experiment results indicate that the diffusion flame has a cone?shape contour,the distance of secondary ignition of boron particles is longer and the pressure of combustion chamber in the same location is higher when the air inlet velocity is approximate to the gas velocity.The contour of the diffusion flame is determined by the approximate level of air inlet velocity and the primary gas velocity and the results of numerical simulation are basically matched with the experiment outcome.