Calculation of particle trajectories in solid-rocket motors with arbitrary acceleration
Calculation of particle trajectories in solid-rocket motors with arbitrary acceleration
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DOI：
10.2514/3.23579
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发表时间：
1992-09
影响因子：
1.9
通讯作者：
J. Sabnis;F. D. Jong;H. Gibeling
中科院分区：
文献类型：
--
作者：
J. Sabnis;F. D. Jong;H. Gibeling
采用欧拉-拉格朗日联合分析方法模拟了多种加速条件下固体火箭发动机中粒子的轨迹。该分析使用连续相的整体平均Navier-Stokes方程的数值解，再加上离散（颗粒）相的拉格朗日分析来模拟两相内部流。线性化块隐式格式用于求解连续相的控制方程，该格式允许使用具有子层分辨率的高度拉伸网格。在计算坐标空间中跟踪粒子的运动，从而提高计算效率。控制方程在广义非惯性坐标系下进行，便于考虑电机加速度的影响。虽然该分析允许完全耦合计算，但本研究忽略了参与相对气相流场的影响。计算了在特定加速度条件下的粒子轨迹，包括轴向加速度、轴向加速度和侧向加速度，以及串联脉冲火箭发动机的离心试验。计算结果表明，加速效应强烈影响粒子对发动机壳体和喷管的撞击形态。
The particle trajectories in a solid-rocket motor under several acceleration conditions have been simulated using a combined Eulerian-Lagrangian analysis. This analysis uses the numerical solution of ensemble-averaged Navier-Stokes equations for the continuous phase, coupled with a Lagrangiah analysis for the discrete (particulate) phase to simulate the two-phase internal flow. A Linearized Block Implicit scheme is used to solve the governing equations for the continuous phase, which allows the use of a highly stretched grid with sublayer resolution. The motion of the particles is tracked in computational coordinate space resulting in computational efficiency. The governing equations are written in generalized noninertial reference frame so that effect of motor acceleration can be easily included. While the analysis allows complete-coupled calculations, the present study has neglected the effect of the participate phase on the gas-phase flowfield. Particle trajectories under specified acceleration conditions, that include axial acceleration, axial and lateral acceleration, as well as a centrifuge test for a tandem pulse rocket motor have been calculated. The calculated results indicate that the acceleration effects strongly influence the particle impingement patterns on the motor case and the nozzle.