摘要
基于磁流体动力学控制方程,在Fluent中添加用户自定义函数(UDF)实现添加特殊源项和自定义标量,对电弧加热等离子体射流流动特性进行了数值模拟。采用不同湍流模型时计算得到氢等离子体射流速度场与温度场,探讨了发动机内速度场与温度场的变化规律,分析了中心轴线上的温度、速度分布,并与文献中同等条件下的实验结果进行对比。计算结果表明:采用标准k-ε模型和标准k-ω模型时与实验结果相差较大,而采用剪切应力传输(SST)k-ω模型时模拟的结果与实验结果较吻合,最大误差约为9.3%。因此采用SSTk-ω模型模拟电弧加热等离子体射流时,更能体现等离子体射流核心区层流这一物理特性。
The axial distributions of the flow field and temperature field in the hydrogen plasma jet,dedicated to rocket thruster,was empirically approximated,mathematically formulated with the three well-recognized turbulence models,theoretically analyzed on the basis of magnetrohydrodynamic（ MHD） control equations,numerically simulated by the software Fluent added with the user-defined functions and scalar,and compared with the experimental results reported in literature under the same operation conditions. The simulated results show that when it comes to discrepancy between the simulated and experimental results,shear-stress-transport（ SST） k- ωmodel,outperforms both the standard k- εmodel and the standard k- ωmodel,because its largest error,about 9. 3%,is much smaller than those of the other two models. We suggest that SSTk- ω model may better describe the laminar flow characteristics in the plasma-jet core region.
出处
《真空科学与技术学报》
EI
CAS
CSCD
北大核心
2015年第10期1220-1224,共5页
Chinese Journal of Vacuum Science and Technology
基金
CAST创新基金项目(No.CAST201228)
