The optimization of a jet turbojet engine by PSO and searching algorithms

The turbojet engine operates on the ideal Brayton cycle (gas turbine) and consists of six main parts: diffusers, compressors, combustion chambers, turbines, afterburners nozzles. Using computer code writing in MATLAB software environment, exergy analysis all selected components, J85-GE-21 for selective height 1000-8000 meters above sea level at speeds 200 m/s temperatures 10°C, 20°C 40°C have been provided then, according to system functions, is optimized based PSO method. For purpose optimization, variables Mach number, efficiency compressor, turbine, nozzle compressor pressure ratio are considered range 0.6 1.4, 0.8 0.95, 0.95 7 10, respectively. highest different parts with an inlet air velocity corresponds a diffuser 73.1%. Then, chamber respectively 68.6% 51.5%. lowest related 4%. After that, afterburner ranked second 11.6%. Also, values entropy produced law before optimization were 1176.99 479 w/k same after 1129 51.4 which identified. process, amount reduced thermodynamics has increased.