نوع مقاله : مقاله پژوهشی
نویسندگان
1 پردیس علوم و فناوریهای نوین، دانشکده مهندسی هوافضا، دانشگاه سمنان، سمنانف ایران
2 گروه مهندسی هوافضا، پردیس علوم و فناوریهای نوین، دانشگاه سمنان، سمنان، ایران
چکیده
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
In this paper, a turbofan engine with double bypass duct (DBP) was studied at design point and off-design conditions. This engine is a separate exhaust, two spool turbofan engine with bleed, turbine cooling, power extraction, and convergent exhaust nozzles. Bypass ratio of main and secondary duct is equal one. Also, a typical turbofan engine with one bypass duct is considered as the benchmark case (simple engine) and its bypass ratio is 2. Simulation results show that DBP engine produces 5/4% thrust more than simple engine at M=0/8 and altitude 9296/4 m (design point). DBP engine thrust is more than simple engine at SL altitude and 9296/4 m at off-design conditions in all flight Mach numbers ranging from 0 to 0/8. Moreover, double bypass duct engine SFC is lower than simple engine at pre-mentioned off-design conditions. Thrust per mass flow rate (F/m ̇) was also studied. By increasing F/m ̇, specific fuel consumption is decreased for both engine types. Another interesting finding is that at constant F/m ̇, DBP engine SFC is lower than simple engine at all flight altitudes.
کلیدواژه‌ها [English]
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