چکیده

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=0.2,R=D/2=0.2, H=0.3, R=D/2=0.2 and H=0.4, R=D/2=0.2 cm at BR=3.18 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 6.2.26. 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 47% near the wall surface and an average of 35% in depth of combustor simulator

کليدواژه ها

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

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احسان کیانپور , 1400 , تجزیه و تحلیل ترمودینامیکی خنک کننده فیلم از هیل های ترانشه دار کروی ترکیبی در انتهای شبیه ساز احتراق , نهمین کنفرانس سوخت و احتراق ایران