Abstract

This study was performed to investigate the effects of cylindrical and row trenched cooling holes with alignment angles of 0° and 90° at blowing ratio of 3.18 on the film cooling performance adjacent to the endwall surface of a combustor simulator. In this research a three-dimensional representation of Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2. The analysis has been carried out with Reynolds-Averaged Navier–Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. Film cooling was placed along the combustor liner walls. In comparison with the baseline case of cooling holes, the application of a row trenched hole near the endwall surface doubled the performance of film cooling effectiveness.