Thermodynamic analyses of film cooling from compound spherical trenched hoes at the end of combustor simulator

The major effects of cylindrical and spherical trenched cooling holes with distance between the hole surface and the combustion chamber panel and the filler diameter on the spherical hole contact surface and the panel surface H=۰.۲,R=D/۲=۰.۲, H=۰.۳, R=D/۲=۰.۲ and H=۰.۴, R=D/۲=۰.۲ cm at BR=۳.۱۸ on the film cooling effectiveness near the combustor end wall surface is an important subject to study in detail. This research included a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT ۶.۲.۲۶. This analyze was done with RANS turbulence model on internal cooling passages. This combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. In comparison with the baseline case, the application of trenched holes increased the effectiveness of film cooling up to ۴۷% near the wall surface and an average of ۳۵% in depth of combustor simulator.

کلیدواژه ها:

Gas Turbine Engine ، Film-Cooling ، Trench Hole ، Dilution Hole