颗粒参数对轴对称超声速气固两相流喷管性能的影响研究

Effects of Particle Parameters on Performance of Axisymmetric Supersonic Gas-Solid Two-Phase Flow Nozzle

关键词:  固体火箭超燃冲压发动机  超声速喷管  气固两相流  颗粒参数  数值仿真

Key words:  Solid-fueled scramjet  Supersonic nozzle  Gas-solid two-phase flow  Particle parameters  Numerical simulation

摘要:

为了探究凝相颗粒参数对固体火箭超燃冲压发动机尾喷管性能的影响规律，本文使用数值仿真方法，研究了颗粒的粒径、温度、入射角度及入射部位对轴对称超声速两相流喷管性能的影响。采用轴对称RANS控制方程和SST k-ω湍流模型模拟气相流场，颗粒轨迹则利用欧拉-拉格朗日方法计算。通过与文献试验结果对比，验证了数值方法的有效性。结果表明，增强两相之间的能量交互作用，是提高喷管性能的根本原因。减小颗粒粒径、提高颗粒温度、增大颗粒入射角和颗粒入射部位靠近壁面，均能增强两相之间的能量交互作用。其中，颗粒粒径变化对性能的影响最大，达到9%左右；颗粒温度次之，约为3%；颗粒入射角和入射区域对性能的影响较小，分别为1.2%和1.4%左右。

Abstract:

To explore the influence of particle parameters on the performance of solid rocket scramjet nozzle， the effects of particle size， temperature， injection angle， and injection position on the performance of axisymmetric supersonic gas-solid two-phase flow nozzle were studied numerically. Axisymmetric RANS equations coupled with shear stress transport k-ω turbulence model were employed to simulate the aerodynamics. The Euler-Lagrange approach was used to calculate the particle trajectories. Accuracy of the numerical method was validated by the experimental data from literature. The results show that enhancing the energy interaction between gas and solid phases is the fundamental reason to improve the performance of the nozzle. Decreasing particle size， increasing particle temperature， increasing particle injection angle and moving particle injection region close to the wall can all enhance the energy interaction. The change of particle size has the greatest impact on the performance， which is about 9%， followed by the particle temperature with about 3%. The injection angle and injection position have little effect on the performance， which are about 1.2% and 1.4% respectively.