A gas turbine unit receives air at 1 bar and 300K and compresses it adiabatically to 6.20 bar. The compressor efficiency is 88%. The fuel has a heating value of 44186 kJ/kg and the fuel air ratio is 0.017 kg fuel/kg of air. The turbine internal efficiency is 90%. Calculate the work of turbine and Compressor per kg of air compressed and thermal efficiency. For products of combustion CP = 1.147 kJ/kg K, $\gamma$ = 1.333.