کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
7046555 1457100 2018 54 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Numerical investigations into heat transfer and film cooling effect on a transonic blade endwall
ترجمه فارسی عنوان
بررسی عددی انتقال حرارت و اثر خنک کننده فیلم بر روی یک انتهای ورق تراون تراس
موضوعات مرتبط
مهندسی و علوم پایه مهندسی شیمی جریان سیال و فرایندهای انتقال
چکیده انگلیسی
The RANS (Reynolds Averaged Navier-Stokes) equations were numerically solved to investigate the heat transfer and film cooling effect on the first stage rotor blade endwall in NASA transonic gas turbine. To reduce the thermal load on the upstream of leading edge, shoulder area and corner area of endwall, different film cooling strategies were presented to evaluate the Stanton number, film cooling effectiveness on endwall and also the aerodynamic performance in cascade at three blowing ratios. Through the film cooling upstream leading edge, the area-averaged St on blade endwall is reduced by 1.4% compared with no film cooling case. Through the shoulder area film cooling, the area-averaged St number on endwall is reduced by 1%, and the area-averaged film cooling effectiveness is increased by 44.4% at M = 0.5. With double hole-arrays at the corner area, the area-averaged St number on the endwall can be reduced by 1-2%, and the area-averaged film cooling effectiveness can be improved by 10.2-13.6%. The energy loss coefficient in the cascade is almost not affected by the blowing ratio for the leading edge and shoulder area film cooling configurations, while it is sensitive to the blowing ratio for the corner area film cooling.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Applied Thermal Engineering - Volume 129, 25 January 2018, Pages 934-952
نویسندگان
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