This study delves into the performance characteristics of a turbojet engine, focusing on the impact of varying compressor pressure ratios and component geometries on thrust and exergy efficiency. The effects of Mach number and compressor pressure ratio on exergy utilisation efficiency at varying altitude values are also examined. Utilising the MATLAB, the analysis was conducted within a range of sea level to 12,000 m altitude. The results obtained provide valuable insights into the potential for optimising turbojet engine performance through strategic adjustments to pressure ratios and component geometries.
Akbas et al. (Thu,) studied this question.