Exergoeconomic analysis of aircraft gas turbine engine

Exergy analysis has been widely used in the design, modeling and performance evaluation of thermal systems. In this thesis, a detailed exergoeconomic analysis was performed for a turbofan engine with a high by-pass ratio used in aircrafts. The turbofan engine consists of 1 stage of fan, 3 and 14 stages of low and high pressure compressors, an annular type combustion chamber, 2 stages of high pressure and 4 stages of low pressure turbines. It has a thrust of 48.04 kN and a specific fuel consumption of 63 kg/hkN at an altitude of 10,670 m. The exergy efficiency values were calculated to be 40.19% for the fan (fan thrust = 36.03 kN) and 15.68% for exhaust (exhaust thrust = 12.04 kN) thrusts. The highest exergy destruction occured in the combustion chamber at 14.75 MW followed by the fan at 2.77 MW. Three new parameters, the product exergy factor, the relative exergy difference and the specific thrust cost (STC), were also proposed. The STC values for the fan and exhaust were obtained to be 139.01 $/hkN and 306.44 $/hkN, respectively. It is expected that, among the three parameters proposed, particularly, the STC would be used to compare and classify aircraft gas turbine engines instead of specific fuel consumption parameter since it includes both energetic and exergetic aspects. Keywords: Aircraft Engines, Exergoeconomics, Exergy, Performance Evaluation