Numerical computations of turbine blade aerodynamics; comparison of LES, SAS, SST, SA and k-e

Numerical investigations of turbine blade are carried out using large-eddy simulation (LES), Scale Adaptive Simulation (SAS), k-ε with extended wall function, Spalart-Allmaras (SA), and Shear Stress Transport (SST). The goal of the present studies is to investigate the turbine blade aerodynamics. The simulations are performed for a Reynolds number, Re = 3.67 x 106, based on the chord, c, of the airfoil and free-stream velocity. The computational results reveal the dissipative nature, of SAS, associated with the turbulence modeling. © 2011 by Marcel Ilie. Published by the American Institute of Aeronautics and Astronautics, Inc

Aerodynamic Aspects and Cooling Techniques of Turbine Blade; Numerical Studies using LES, SAS, SST, SA and k-e

Numerical investigations of turbine blade are carried out using large-eddy simulation (LES), Scale Adaptive Simulation (SAS), k-ε with extended wall function, Spalart-Allmaras (SA), and Shear Stress Transport (SST). The goal of the present studies is to investigate the turbine blade aerodynamics and blade cooling techniques. The simulations are performed for a Reynolds number, Re = 3.67 x 106, based on the chord, c, of the airfoil and free-stream velocity. The computational results reveal the dissipative nature, of SAS, associated with the turbulence modeling. © 2011 by Marcel Ilie. Published by the American Institute of Aeronautics and Astronautics, Inc

Icing Effect on the Aerodynamics of Wind Turbines: A Numerical Study Using Large-Eddy Simulation

The influence of icing effect on the aerodynamics of wind turbine is investigated using large-eddy simulation (LES). The simulations are performed for a Reynolds number, Re = 1.3 × 106, based on the chord, c, of the airfoil (NACA0012). Computations are carried out to investigate the influence of the icing effect on the aerodynamic coefficients. The study reveals that the icing effect influences the aerodynamic coefficients in a specific manner. Larger amplitudes of aerodynamic coefficients were observed for the case of an iced leading edge when compared with the clean NACA0012 case. © 2010 by Marcel Ilie