Assessment of turbulence modeling for gas flow in two-dimensional convergent–divergent rocket nozzle
Assessment of turbulence modeling for gas flow in two-dimensional convergent–divergent rocket nozzle
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DOI：
10.1016/j.apm.2011.01.013
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发表时间：
2011-07
影响因子：
5
通讯作者：
A. Balabel;A. Hegab;M. Nasr;S. El-Behery
中科院分区：
文献类型：
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作者：
A. Balabel;A. Hegab;M. Nasr;S. El-Behery
在本研究中，在二维收敛-扩张火箭喷管的湍流气体流动动力学的数值预测和相关的物理现象进行了研究，为各种操作条件。假设喷嘴具有不渗透和绝热壁，上游侧有整流器，并连接到围绕喷嘴几何形状并沿下游方向延伸的增压室。在该模型中，进口流场被假定为二维、定常、可压缩、亚音速湍流。所考虑的流动的基于物理的数学模型由质量守恒、动量和能量方程组成，其受到由上述物理问题定义的适当边界条件的约束。使用不同的湍流模型对具有湍流效应的控制方程组进行数值求解，以证明其在预测此类复杂几何形状中湍流气体流动特性时的数值准确性。采用不同的湍流模型的性能进行了评估，通过比较所获得的结果的静态壁压和激波位置与现有的实验和数值数据。计算了喷管壁面和分离点处的无量纲剪应力，并给出了流场图。各种实现的湍流模型显示了不同的湍流特性。然而，剪切应力输运（SST）的k-ω模型表现出最好的整体协议与实验测量。在一般情况下，建议的数值方法应用在本文件中显示出良好的能力，在预测的物理现象和流动特性遇到的这种复杂的湍流。
In the present study, the turbulent gas flow dynamics in a two-dimensional convergent–divergent rocket nozzle is numerically predicted and the associated physical phenomena are investigated for various operating conditions. The nozzle is assumed to have impermeable and adiabatic walls with a flow straightener in the upstream side and is connected to a plenum surrounding the nozzle geometry and extended in the downstream direction. In this integrated component model, the inlet flow is assumed a two-dimensional, steady, compressible, turbulent and subsonic. The physics based mathematical model of the considered flow consists of conservation of mass, momentum and energy equations subject to appropriate boundary conditions as defined by the physical problem stated above. The system of the governing equations with turbulent effects is solved numerically using different turbulence models to demonstrate their numerical accuracy in predicting the characteristics of turbulent gas flow in such complex geometry. The performance of the different turbulence models adopted has been assessed by comparing the obtained results of the static wall pressure and the shock position with the available experimental and numerical data. The dimensionless shear stress at the nozzle wall and the separation point are also computed and the flow field is illustrated. The various implemented turbulence models have shown different behavior of the turbulent characteristics. However, the shear-stress transport (SST) k–ω model exhibits the best overall agreement with the experimental measurements. In general, the proposed numerical procedure applied in the present paper shows good capability in predicting the physical phenomena and the flow characteristics encountered in such kinds of complex turbulent flow.