Numerical investigation of effusion cooling in gas turbine combustor liner

Abstract

In this study, a numerical analysis was performed to find the aerothermal characteristics of the effusion cooled gas turbine combustor liner. The analyzed geometric model is a scale model of an actual combustor liner. The study aims to investigate the effect of different blowing ratios by validating an experimental test setup. In experimental studies on effusion cooling, the sidewall effect is a serious problem that can distort the results. Numerical analyses provide advantages in visualizing temperature and velocity contours in different sections of physical model. The counter rotating vortex pairs, the horseshoe vortex and the recirculation zone are the main flow features of the jet mixture. At a blowing ratio of 3.35, numerical analyzes gave the highest value of cooling effectiveness. Although the blowing ratio slightly changes the cooling effectiveness in experimental data, it has been found that the effect of blowing ratio is more pronounced on the numerical results, especially at high blowing ratios.