development of advanced film cooling with row trenched holes configuration at the end of combustor simulator

The major effects of cylindrical and row trenched cooling holes with different alignment angles of 0, ±60 and 90 degrees at br=3.18 on the effectiveness of film cooling near the combustor end wall surface is an important subject to study. the gas turbine industry is trying to expand the performance of the gas turbine engine. according to well-known brighton cycle, the combustion outlet temperature must increase to achieve a higher efficiency. however, increasing the turbine inlet temperature creates an unfavorable environment for downstream components. this requires the design of an efficient cooling method in this area. in a traditional cooling system, increasing the blow ratio increases the cooling efficiency. but the coolant does not attach well on the protected surface at higher blowing ratios. this requires changing the structure of the cooling holes. in the current study, researchers used a fluent package 6.2.26 to simulate a 3-d model of a pratt and whitney gas turbine engine. in this research, a rans model was used to analyze the flow behavior on the passageways of internal cooling. in the combustor simulator, the dilution jets and cooling flow staggered in the streamwise direction and aligned in the spanwise direction as well. in comparison with the baseline case of cooling holes, the application of row trenched hole near the end wall surface increased the effectiveness of film cooling from 75% to 100% for different trench cases.