Implicit Solution of Preconditioned Navier-Stokes Equations Using Algebraic Multigrid

AIAA Journal ◽  
10.2514/2.689 ◽  
1999 ◽  
Vol 37 (1) ◽  
pp. 29-36 ◽  
Author(s):  
Jonathan M. Weiss ◽  
Joseph P. Maruszewski ◽  
Wayne A. Smith
Keyword(s):  
Stokes Equations ◽  
Algebraic Multigrid ◽  
Navier Stokes ◽  
Navier Stokes Equations

scholarly journals Algebraic multigrid for the finite pointset method

2020 ◽  
Vol 23 (1-4) ◽  
Author(s):  
Bram Metsch ◽  
Fabian Nick ◽  
Jörg Kuhnert
Keyword(s):  
Differential Operators ◽  
Stokes Equations ◽  
Algebraic Multigrid ◽  
Navier Stokes ◽  
Symmetric Matrices ◽  
Point System ◽  
Navier Stokes Equations ◽  
Saddle Point System ◽  
Matrix Property ◽  
Velocity Pressure

AbstractWe investigate algebraic multigrid (AMG) methods for the linear systems arising from the discretization of Navier–Stokes equations via the finite pointset method. In the segregated approach, three pressure systems and one velocity system need to be solved. In the coupled approach, one of the pressure systems is coupled with the velocity system, leading to a coupled velocity-pressure saddle point system. The discretization of the differential operators used in FPM leads to non-symmetric matrices that do not have the M-matrix property. Even though the theoretical framework for many AMG methods requires these properties, our AMG methods can be successfully applied to these matrices and show a robust and scalable convergence when compared to a BiCGStab(2) solver.

Implicit solution of preconditioned Navier-Stokes equations using algebraic multigrid

AIAA Journal ◽  
1999 ◽  
Vol 37 ◽  
pp. 29-36 ◽  
Author(s):  
Jonathan M. Weiss ◽  
Joseph P. Maruszewski ◽  
Wayne A. Smith
Keyword(s):  
Stokes Equations ◽  
Algebraic Multigrid ◽  
Navier Stokes ◽  
Navier Stokes Equations

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

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