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Performance Analysis of a Separate-Exhaust Twin-Spool Turbofan EngineUsing a Secondary Combustion Chamber

عنوان مقاله: Performance Analysis of a Separate-Exhaust Twin-Spool Turbofan EngineUsing a Secondary Combustion Chamber
شناسه ملی مقاله: AEROSPACE22_007
منتشر شده در بیست و دومین کنفرانس بین المللی انجمن هوافضای ایران در سال 1402
مشخصات نویسندگان مقاله:

Reza Modanlou - Department of Aerospace Engineering, Faculty of New Sciences and Technologies, Semnan University,Semnan, Iran
Elyas Lekzian - Department of Aerospace Engineering, Faculty of New Sciences and Technologies, Semnan University,Semnan, Iran

خلاصه مقاله:
In this paper, a separate-exhaust twin-spool turbofan engine with a secondary combustion chamber is studied. aerothermodynamic simulation is used to study the performance of this engine. A simulation code is developed in MATLAB which predicts the on-design and off-design performance of innovative engine layouts. For the off-design simulation, the referencing method is utilized. The simulation results demonstrate that at sea level static condition, elevation of second combustion chamber temperature to ۱۵۰۰ K can increase the thrust ۱۶% at the cost of ۱۲% increase in SFC. Moreover, flat rate analysis shows that temperature at which the thrust reaching its maximum is increased to ۳۱۳ K when T ⁄T , = ۰.۸۸. Also, by increasing the second combustion chamber temperature, the engine thrust at altitude ۱۰.۶۷ km and M=۰.۸ is promoted and, SFC is increased too. The engine overall efficiency is for the engine with secondary chamber is generally lower than the conventional engine without secondary chamber.

کلمات کلیدی:
Turbofan – Secondary Combustion chamber – Performance – Flat rate.

صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/2058538/