In a gas turbine cycle, the condition of air at the entrance of compressor is 1 bar and \(27^{\circ} \mathrm{C}\). Pressure ratio is 6 . Maximum temperature is \(700^{\circ} \mathrm{C}\). The exhaust pressure of turbine is 1 bar. Assume \(100 \%\) efficiency of compressor and \(95 \%\) efficiency of both turbines and combustion, fall in pressure through combustion chamber is \(0.1 \mathrm{bar}\), calculate: (i) thermal efficiency, (ii) work ratio, (iii) heat rate, (iv) air-rate in \(\mathrm{kg} / \mathrm{kW}\), (v) specific fuel consumption, and (vi) the air-fuel ratio.

\(C_{p}=1.005 \mathrm{~kJ} / \mathrm{kg}\)

\(C_{p g}=1.147 \mathrm{~kJ} / \mathrm{kg}\)

\(C_{V}=42,700 \mathrm{~kJ} / \mathrm{kg}\)