flow and heat transfer analyses of film injectant from rows of trenched holes at the end of combustor simulator

Gas turbine industries are using the well-known brayton cycle and increases the combustion outlet temperature to expand the performance of the gas turbine engine. however, increased turbine inlet temperature creates a harsh environment for downstream components. this requires the design of an efficient cooling technique. in a traditional cooling, the coolant does not attach well on the surface at higher blow ratios. this requires changing the structure of the cooling holes. a useful way would be to trench the cooling holes and align the trenched holes in a row. the effects of cylindrical and row cooling holes with different alignment angles of 0, ±60 and 90 degrees at br=1.25 and br=3.18 on the film cooling effectiveness is an important issue that needs to be studied. in the present study, the researchers used the fluent 6.2.26 to simulate a 3d model of a pratt and whitney gas turbine engine. in this research, rans model was used to analyze the flow behavior in internal cooling passages. in comparison with the baseline case of cooling holes, the application of trenched cases increased the film cooling effectiveness from 8% to 200%.