Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degree at Different Blowing Ratios

摘要

This study was carried out to find out the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling performance adjacent the combustor endwall, whereas two different cooling holes arrangements as cylindrical and row trenched cooling holes with alignment angle of 90 degree are considered. In this research, a three-dimensional presentation of a true Pratt and Whitney aero-engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26 to gain fundamental data. 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, which were staggered in the stream wise direction and aligned in the span wise direction. The entire findings of the study declared that with using the row trenched holes near the enwall surface; film cooling effectiveness is doubled compared to the cooling performance of baseline case.