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An exergy analysis is reported of a J85-GE-21 turbojet engine and its   components for two altitudes: sea level and 11,000 meters. The turbojet   engine with afterburning operates on the Brayton cycle and includes six main   parts: diffuser, compressor, combustion chamber, turbine, afterburner and   nozzle. Aircraft data are utilized in the analysis with simulation data. The   highest component exergy efficiency at sea level is observed to be for the   compressor, at 96.7%, followed by the nozzle and turbine with exergy   efficiencies of 93.7 and 92.3%, respectively. At both considered heights,   reducing of engine intake air speed leads to a reduction in the exergy   efficiencies of all engine components and overall engine. The exergy   efficiency of the turbojet engine is found to decrease by 0.45% for every 1°C   increase in inlet air temperature

Exergetic analysis of an aircraft turbojet engine with an afterburner