Combustion gases enter a gas turbine at 900C, 800 kPa, and 100 m/s and leave at 650C,

Question:

Combustion gases enter a gas turbine at 900°C, 800 kPa, and 100 m/s and leave at 650°C, 400 kPa, and 220 m/s. Taking cp = 1.15 kJ/kg·°C and k = 1.3 for the combustion gases, determine
(a) The exergy of the combustion gases at the turbine inlet and
(b) The work output of the turbine under reversible conditions.
Assume the surroundings to be at 25°C and 100 kPa. Can this turbine be adiabatic?