A Comparison of Cylindrical and Row Trenched Film-Cooling Holes on a Combustor Endwall Surface at High Blowing Ratio
Keywords:gas turbine engine, film-cooling, cylindrical hole, trench hole, dilution hole
This study was done to study the effects of cylindrical and row trenched cooling holes with alignment angle of ±60 degrees at blowing ratio of BR=3.18 on the film cooling effectiveness near the combustor end wall surface. In this study, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analysed with a commercial finite volume package FLUENT 6.2.26. 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. In comparison with the baseline case of cooling holes, the application of row trenched hole near the endwall surface doubled the performance of film-cooling effectiveness.