摘要
在对跨音速压气机级的动／静双叶排中的三维定常紊流流场数值的模拟中，利用三阶高分辨率ＮＮＤ格式和ＬＵ－ＳＧＳ隐式推进迭代法，既保证了流场中激波的模拟质量和粘性流动特征的正确预估，也实现了求解过程的高效率。对某单级跨音速压气机的计算及其与实验数据的对比证实了本文方法的有效性。
An implicit Navier-Stokes solver is presented for numerical simulation of three-dimensional steady compressible turbulent flow in a transonic compressor stage.The LU-SGS(Low-Upper Symmetric-Gauss-Seidel)implicit time-marching scheme developed by Jameson and Yoon is used to improve the computational efficiency.In order to obtain distinct shock system and valid boundary layer characteristics,one kind of high resolution schemes,the third order accurate NND (Non-oscillatory,Non-free-parameter,Dissipative)scheme is incorporated in this solver.The governing equations,the numerical scheme,the grid system and the boundary treatment method are considered in this paper.The Baldwin-Lomax Algebra model is utilized to compute the turbulent viscosity.The viscous flow in a single stage transonic compressor is calculated by this solver.The calculation was performed by coupling the rotor and stator flow fields at each time step through an overlapped grid.The computed results were compared with experiment data.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1996年第4期369-372,共4页
Journal of Aerospace Power
基金
国家自然科学基金
航空科学基金
关键词
三维流动
紊流流动
跨音速
压气机
Three-dimensional flows Turbulent flow High resolution Numerical analysis Transonic compressors
