TY - JOUR
TI - Exergetic analysis of an aircraft turbojet engine with an afterburner
AU - Ehyaei Mehdi Ali
AU - Anjiridezfuli Abdolhasan
AU - Rosen Marc A
JN - Thermal Science
PY - 2013
VL - 17
IS - 4
SP - 1181
EP - 1194
PT - Article
AB - 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.