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为研究高含铝推进剂低压固体火箭发动机的尾流场特性,利用流体计算软件Fluent,采用三维雷诺平均N-S方程和标准k-ε湍流模型,对高含铝固体推进剂低压发动机尾流场复燃进行了数值模拟和实验研究。结果表明:低压下高含铝固体推进剂羽流复燃时,温度分布呈现“双峰”的现象,第一温峰是纯气相燃烧形成的,第二温峰是铝粒子燃烧形成的;且铝粒径越小,第二温峰出现的位置离喷管越近,铝粒子温度越高,最高可达1124K;燃烧室压强越高,第二温峰出现的位置离喷管越远。发动机试车试验中也出现“双峰”的羽流温度场,且测得粒子最高温度为1141K,与模拟结果吻合较好。
In order to study the wake field characteristics of low-pressure solid rocket motor with high-aluminum-containing propellant, three-dimensional Reynolds averaged Navier-Stokes equations and standard k-ε turbulence model were used to calculate the wake field of low-pressure solid rocket propellant Burning numerical simulation and experimental study. The results show that when the plume of aluminum-containing solid propellant is re-ignited at low pressure, the temperature distribution shows a phenomenon of “double peak”. The first temperature peak is formed by pure gas combustion, and the second temperature peak is formed by combustion of aluminum particles ; And the smaller the aluminum particle size, the second temperature peak appears closer to the nozzle, the higher the aluminum particle temperature is up to 1124K; the higher the combustion chamber pressure, the second temperature peak appears farther away from the nozzle . The “Twin Peak” plume temperature field also appeared in the test run of the engine, and the maximum temperature of the particles was found to be 1141K, which was in good agreement with the simulation results.