铝冰发动机内流场的数值计算

为了使用数值模拟的方法计算铝冰发动机的性能,用颗粒表面反应模型和气相反应模型模拟铝颗粒在铝冰发动机燃烧室中与水蒸气的燃烧过程,用欧拉-拉格朗日方法计算颗粒沿轨迹的参数,分析了数值模拟的结果,并进行了相同尺寸的铝冰发动机实验,把数值模拟结果与实验结果进行了比较。数值计算得到的燃烧室稳态工作压强约为9.38 MPa,与实验结果接近,燃烧室平均温度为2950.65 K,相比热力计算得到的推进剂燃烧温度略低。通过对铝冰发动机的内流场数值计算,得到了与实验相符合的结果,验证了数值计算模型的有效性。

Numerical simulation of aluminum-ice solid propellant motor

To calculate the theoretical performance of the Aluminum-Ice Solid Rocket Motor(ALICE SRM),the particle surface reaction model and the gas phase reaction model were used to simulate the burning process of aluminum particle and the steam in the combustion chamber of the ALICE SRM.The Euler-Lagrange model was used to calculate the particle parameters along their trajectories.The numerical results were analyzed and compared with the experimental results of the same sized ALICE SRM.The numerical chamber pressure of the ALICE SRM is about 9.38 MPa,which is very close to the experimental value.The calculated average chamber temperature is 2950.65 K,which is lower than that of the thermo-chemistry calculation result.By the numerical simulation of the internal flow-field of the ALICE SRM,a good agreement between the numerical results and the experimental data was obtained,which clearly verified the numerical models in predicting ALICE SRM performance.