应用Steger-Warming通量分裂技术,将守恒型方程中的流通向量分裂成两部分,应用NND(non-oscillatory,containing no free parameters and dissipative)格式对无黏项进行数值离散,黏性项采用中心差分格式,采用LU-SGS(lower-upper symmetri...应用Steger-Warming通量分裂技术,将守恒型方程中的流通向量分裂成两部分,应用NND(non-oscillatory,containing no free parameters and dissipative)格式对无黏项进行数值离散,黏性项采用中心差分格式,采用LU-SGS(lower-upper symmetric Gauss-Seidel)隐式推进迭代建立了跨声速轴流压气机性能及内流场三维Navier-Stokes方程的高分辨率和高效率的数值方法.数值模拟给出NASA rotor 37和NASArotor 67性能及内流场流动结构.并进一步基于混合平面法建立了多级轴流压气机性能计算模型,详细分析了某一级跨声速轴流压气机性能和内流特性,计算与实验结果比较表明了本模型与方法是可行的和可靠的.展开更多
The steady calculation based on the mixing-plane method is still the most widely-used three-dimensional flow analysis tool for multistage turbomachines. For modern turbomachines,the trend of design is to reach higher ...The steady calculation based on the mixing-plane method is still the most widely-used three-dimensional flow analysis tool for multistage turbomachines. For modern turbomachines,the trend of design is to reach higher aerodynamic loading but with still further compact size. In such a case, the traditional mixing-plane method has to be revised to give a more physically meaningful prediction. In this paper, a novel mixing-plane method was proposed, and three representative test cases including a transonic compressor, a highly-loaded centrifugal compressor and a highpressure axial turbine were performed for validation purpose. This novel mixing-plane method can satisfy the flux conservation perfectly. Reverse flow across the mixing-plane interface can be resolved naturally, thus making this method numerically robust. Artificial reflection at the mixing-plane interface is almost eliminated, and then its detrimental impact on the flow field is minimized. Generally, this mixing-plane method is suitable to simulate steady flows in highly-loaded multistage turbomachines.展开更多
文摘The steady calculation based on the mixing-plane method is still the most widely-used three-dimensional flow analysis tool for multistage turbomachines. For modern turbomachines,the trend of design is to reach higher aerodynamic loading but with still further compact size. In such a case, the traditional mixing-plane method has to be revised to give a more physically meaningful prediction. In this paper, a novel mixing-plane method was proposed, and three representative test cases including a transonic compressor, a highly-loaded centrifugal compressor and a highpressure axial turbine were performed for validation purpose. This novel mixing-plane method can satisfy the flux conservation perfectly. Reverse flow across the mixing-plane interface can be resolved naturally, thus making this method numerically robust. Artificial reflection at the mixing-plane interface is almost eliminated, and then its detrimental impact on the flow field is minimized. Generally, this mixing-plane method is suitable to simulate steady flows in highly-loaded multistage turbomachines.
