Abstract
The turbojet engine is used to propel the aircraft by accelerating the combustion gases in the opposite direction to motion. This is accomplished by greatly accelerating a small mass of fluid. In this work, an energy analysis is carried out under operating conditions of 13000-m altitude and 0.8 Mach number to determine the variation of specific thrust and the specific fuel consumption with different compressor pressure ratios and turbine inlet temperatures. The exergy analysis is then applied to show more realistic performance. Thereby, the specific thrust showed an increase by 1.7%, and the specific fuel consumption was decreased by the same ratio as a result of 10% drop in optimum pressure ratio.
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