多块多重网格法及其跨声速转子内流并行模拟

为提高压气机内部复杂流动计算的收敛速度,发展了一种多块多重网格上的可压缩流动并行计算流体动力学(CFD)方法,数值模拟了跨声速转子NASA Rotor 35内部流动及气动性能,重点分析了对接分区方式和内界面通信模式对并行性能的影响。结果表明:对接分区方法和多块多重网格内界面数据处理方法能够保证串、并行CFD方法结果基本一致,且与实验数据吻合良好;并行精度基本不受分区数目和通信模式的影响,并行效率随着相对通信负载的增大而降低。所发展的并行计算方法对跨声速转子气动分析和设计具有一定的可靠性,为开发大型流体机械复杂流动的基础并行算法及软件提供了参考价值。

Multi-block multi-level grid method and parallel simulation of internal flows of transonic rotor

In order to improve the convergence rate of numerical simulation of complex flow in compressor, a parallel computational fluid dynamics(CFD) method with multi-block multi-level grid was developed in this work. This method was applied to numerically simulate the internal flow fields and aerodynamic performance of the transonic axial compressor NASA Rotor 35, and analyze the influences of patch partitions and interface communication on the parallel performance. Results showed that the developed patch partition method and multi-block multi-level grid interface treatment method ensured the serial and parallel results were the same and both are consistent with the experimental data. The numerical accuracy was not affected by the number of partitions and communication mode, while the parallel efficiency decreased as the relative communication load increased. The developed parallel CFD method was of certain reliability to carry out the aerodynamic analysis and design for transonic axial rotor, and had the reference value to develop the fundamental parallel algorithm and software for the complex flow in large-scale fluid machinery.