The Effects of Row Trench Holes with Alignment Angle of +60 Degrees on Film Cooling Effectiveness at Low Blowing Ratios
Keywords:gas turbine, film cooling, trenched holes, shaped holes, compound holes
This study was accomplished to study the effects of cylindrical and row trenched cooling holes with alignment angle of +60 degrees at low blowing ratio, BR = 1.25 on the film cooling effectiveness near the combustor end wall surface. In this 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. The current study has been performed with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator combined the interaction of two rows of dilution jets that were staggered in the stream wise direction and aligned in the span wise direction, with that of film cooling along the combustor liner walls. The findings of the study declared that by using the row trenched holes near the end wall surface, film cooling effectiveness is doubled compared to the cooling performance of baseline case.