Off-Design Modelling of a Turbo Jet Engine with Operative Afterburner

Gas turbines are considered as one of the leading internal combustion engines in modern air transportation due to its favourable power weight ratio and continuous process. Recent research focus has been concerned with performance improvements aimed at reduced fuel consumption hence impact on environment. This study is using theoretical computational methods model operation a turbojet gas turbine engine. The commercial software GasTurb13 was used for simulation while Microsoft Excel analytical study. solved pseudo-perfect models i.e. component maps since specific could not be inputted into solver. effect changes Mach number altitude engine studied. Also compressor pressure ratio, inlet temperature afterburner exit were also Results obtained showed optimum maximum thrust constraint 16.78 operating (Ma) = 0.8 10,000 m, Turbine (TIT) 1200 K Afterburner 1800 K.