Airfoil design optimization using the Navier-Stokes equations

1994 ◽  
Vol 83 (3) ◽  
pp. 447-461 ◽  
Author(s):  
S. Eyi ◽  
J. O. Hager ◽  
K. D. Lee
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Navier Stokes Equations

High-lift design optimization using Navier-Stokes equations

1996 ◽  
Vol 33 (3) ◽  
pp. 499-504 ◽  
Author(s):  
S. Eyi ◽  
K. D. Lee ◽  
S. E. Rogers ◽  
D. Kwak
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations

scholarly journals Turbine cascade design via multigrid-aided finite-difference progressive optimization

2008 ◽  
pp. 199-215
Author(s):  
Luciano A. Catalano ◽  
Andrea Dadone ◽  
Vito S.E. Daloiso
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Flow Analysis ◽  
Navier Stokes ◽  
Computational Time ◽  
Turbine Cascade ◽  
Navier Stokes Equations ◽  
Fine Mesh ◽  
Sensitivity Derivatives ◽  
Volume Method

This paper proposes an efficient and robust procedure for the design optimization of turbomachinery cascades in inviscid and turbulent transonic flow conditions. It employs a progressive strategy, based on the simultaneous convergence of the design process and of all iterative solutions involved (flow analysis, gradient evaluation), also including the global refinement from a coarse to a sufficiently fine mesh. Cheap, flexible and easy-to-program Multigrid-Aided Finite Differences are employed for the computation of the sensitivity derivatives. The entire approach is combined with an upwind finite-volume method for the Euler and the Navier-Stokes equations on cell-vertex unstructured (triangular) grids, and validated versus the inverse design of a turbine cascade. The methodology turns out to be robust and highly efficient, the converged design optimization being obtained in a computational time equal to that required by 15 to 20 (depending on the application) multigrid flow analyses on the finest grid.

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.

Sign in / Sign up

Export Citation Format

Share Document