跨声速轴流压气机特性全三维黏性流动分析  

Three-dimensional viscous numerical investigations on the overall aerodynamic performance of transonic axial-flow compressors

作　　者：贾海军[1] 吴虎[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2009年第10期2326-2332,共7页Journal of Aerospace Power

摘　　要：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.The internal 3-D viscous flow fields of the transonic axial-flow compressors were numerically analyzed using a time-marching finite difference method.This calculation method was developed by the LU-SGS(lower-upper symmetric Gauss-Seidel) implicit scheme and NND(non-oscillatory,containing no free parameters and dissipative) scheme with Steger-Warming flux vectors splitting technique,and the centered difference scheme was used for the viscous portion.The mixing plane model was employed to simulate the interna...

关 键 词：跨声速轴流压气机 数值模拟 通量分裂技术 混合平面法 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]