Cooling holes with different structures effects on coolant cross flow and heat transfer at the outlet of the combustion chamber

Abstract: The major effects of cylindrical and row trenched cooling holes with angles alpha=30, beta=0, alpha=40, beta=0 alpha=50, at BR=3.18 on the effectiveness film near combustor end wall surface is an important subject to study in detail. In current study, researchers used a FLUENT package 16/11 simulate 3-D model Pratt Whitney gas turbine engine. this research, RNG turbulence K-ε was analyze flow behavior passage ways internal cooling. simulator, dilution jets staggered streamwise direction aligned spanwise as well. comparison baseline case holes, application hole increased up 100% for different trench cases.