The turbofan engine had many developments in the past 60 years and becomes the common power plant employed in both civil airliners and military aircrafts. It combines the advantages of both of turboprop engines (high propulsive efficiency and thrust) and turbojet engines (high flight speed and altitude). To cope with the needs of high thrust forces that propel wide body airliner and increase of their payload and range as well as enlarging mauver capabilities of military aircrafts, successive developments of turbofan engines are needed. These developments in turbofan design have endeavors of larger thrust force, low noise and emission as well as better fuel economy. These goals were achieved by increasing of the bypass ratio (BR), fan pressure ratio (FPR), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper presents a parametric study and design point selection of a high bypass ratio turbofan engine (close to GEnx-1B70). This engine is one of the products of GE Aviation Company. Performance analysis is performed using MATLAB program codes.
Prof. Dr. Bilal BİLGİN