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 ۰, ±۶۰ and ۹۰ degrees at BR=۱.۲۵ and BR=۳.۱۸ on the film cooling effectiveness is an important issue that needs to be studied. In the present study, the researchers used the FLUENT ۶.۲.۲۶ and RANS model to simulate a ۳D model of a Pratt and Whitney gas turbine engine. The results showed that the film cooling layer was increased in the average ۸۹% at high blowing ratio, and thus it enhanced the cooling performance. In addition, compared to the baseline case, the application of trenched cases increased the film cooling effectiveness from ۸% to ۲۰۰%.

کلیدواژه ها:

Gas Turbine Engine ، Film-Cooling ، Trench Hole ، Cross Flow