Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor

Abstract

This research was done to analyze the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling effectiveness at the combustor outlet, whereas the cylindrical and row trench holes with alignment angle of +60 degrees were considered. In the current research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26. This study has been carried out with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. The combustor combines the interaction of two rows of dilution jets, which are staggered in the stream-wise direction and aligned in the span-wise direction, with that of film cooling along the combustor liner walls. The entire findings of the study showed that trenched holes performed much more efficiently at both blowing ratios, especially at BR=3.18.