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