A regenerative gas turbine with intercooling and reheat operatesat steady state (Figure Q2). Air enters the compressor at 100 kPa,27°C with a mass flow rate of 6 kg/s. The pressure ratio across thetwo-stage compressor is 10. The pressure ratio across the two-stageturbine is also 10. The intercooler and reheater each operate at300 kPa. At the inlets to the turbine stages, the temperature is1127°C. The temperature at the inlet to the second compressor stageis 27°C. Assuming the compressors and turbines stages arereversible systems (100% efficiency). The regenerator effectivenessis 70%. Assuming that there is no pressure loss duringintercooling, combustion and reheating process, and by using coldair standard assumption, sketch a T-s diagram for this regenerativeBrayton-cycle and determine;
i) the thermal efficiency,
ii) the net power developed (kW),
iii) back work ratio.
