A gas turbine engine has a pressure ratio of 9.2 to 1. Assume air enters at 25 Celsius and 101 kPa, and that 750 kJ/kg heat are added in the combustion chamber. The compressor and turbine efficiencies are 85% and 89%, respectively. There is a pressure drop in the inlet piping of 2 kpa, a pressure drop in the outlet piping of 3 kPa and a pressure drop in the combustion chamber of 12 kPa. Analyze the cycle using air standard assumptions that account for variation in specific heats. Determine the mass flow rate of air required to produce 60 MW.