Computational Study of Film-Cooling Effectiveness on a Low-Speed Airfoil Cascade: Part II — Discussion of Physics Available to Purchase

Computational fluid dynamics (CFD) results are presented for a study of film cooling on a linear turbine airfoil cascade. The simulations are for a single-row of streamwise-injected cylindrical holes on both the pressure and suction surfaces, downstream of the leading edge. The cases considered match experimental efforts previously documented in the open literature. Results are obtained for density ratio equal to 2.0, and a blowing ratio range from 0.5 to 2.0. The computational methodology minimizes error due to geometry modeling, grid, and numerical scheme, placing the simulations against the limits of the turbulence modeling. In this part, the results are examined in order to highlight the mean-flow physical mechanisms responsible for film-cooling performance on airfoils.