Air enters the compressor of a gas turbine at 100 kPa, 300 K, and a volumetric flow rate of 5.0 m3/s. The air is compressed in two stages to 1200 kPa, with intercooling to 300 K between the stages at a pressure of 350 kPa. The turbine inlet temperature is 1400 K and the expansion occurs in two stages, with reheat to 1340 K between the stages at a pressure of 350 kPa. The compressor and turbine stage efficiencies are 87% and 85%
respectively. Determine:
a) the thermal efficiency of the cycle,
b) the back work ratio,
c) the net power developed, in kW.