The turbofan engine had many developments in the past 60years and becomes the common power plant employed in bothcivil airliners and military aircrafts. It combines the advantagesof both of turboprop engines (high propulsive efficiency andthrust) and turbojet engines (high flight speed and altitude).To cope with the needs of high thrust forces that propel widebody airliner and increase of their payload and range aswell as enlarging maneuver capabilities of military aircrafts,successive developments of turbofan engines are needed. Thesedevelopments in turbofan design have endeavors of larger thrustforce, low noise and emission as well as better fuel economy. Thesegoals were achieved by increasing of the bypass ratio (BR), fanpressure ratio (FPR), overall pressure ratio (OPR), turbine inlettemperature (TIT) as well as using new materials, productionand cooling techniques for both turbines and combustionchamber such modifications led to improvements in thermal,propulsive and overall efficiencies, decreases in thrust specificfuel consumption (TSFC) and increase the specific thrust. Thispaper presents a parametric study and design point selection ofthe cold sections of high bypass ratio turbofan engine (close toGEnx-1B-70). Cold sections include the intake, the fan, and thecompressor. This engine is one of the products of GE AviationCompany. Performance analysis is performed using MATLABprogram code for both taking-off and cruise conditions.
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