Consider an aero gas turbine engine as shown above. Air enters the compressor at a static pressure of 1.1 bar, static temperature of 300 K and a volumetric flow rate of 5 m³/s. The isentropic efficiencies of the compressor and turbine are 83 and 87%, respectively. The compressor pressure ratio is 20 and the static temperature at the turbine inlet is 1400 K. Combustion occurs at constant pressure. Static pressure at the turbine exit is 1.2 bar. Based on an air-standard analysis:
a) Considering just the gas generator, draw the ideal and the actual thermodynamic cycles on an enthalpy-entropy diagram. Clearly label all pressures, specific enthalpies, and specific entropies.
b) Calculate the thermal efficiency of the cycle.
c) Calculate the net power developed, in kW.