A gas turbine inlet receives air at 1 bar and 300 K and compresses it adiabatically to 6 bar. The compressor efficiency is 90% where the fuel has heating value of 44000 kJ/kg and fuel-air ratio is 0.017. The turbine efficiency is 92%. Calculate the work of the turbine and compressor and also find the thermal efficiency. For air cp=1.005 kJ/kg-K, γ=1.4. For products of combustion, cp=1.47 kJ/kg-K, γ=1.33.