THERMODYNAMIC ANALYSIS OF GAS TURBINE

This project is intended to do analysis of a gas turbine engine performance. The gas
turbine operating conditions (pressure ratio, turbine inlet and exhaust temperatures, fuel
to air ratio, isentropic compressor and turbine efficiencies and ambient temperature)
affect the turbine performance. The performance indicators are thermal efficiency,
compressor work, power output, specific fuel consumption and heat rate. This project
will focus on the effect of ambient temperature, turbine inlet temperature, air to fuel ratio
and compression ratio on the efficiency and output power of the turbine. The gas turbine
basic components were modelled based on thermodynamics principle. The developed
components models were integrated using conservation of mass and energy balance. In
solving mathematical equation of every component, Microsoft Office Excel software was
used. The simulation result could be use to suggest the optimum cycle operating
condition.