**Problem 6.13 - An Aircraft Gas Generator
Turbine**

Consider an aircraft adiabatic gas generator turbine operating under the conditions shown in the diagram:

Ignoring kinetic and potential energy changes and assuming that the gas behaves as air with a mass flow rate of 4.55 kg/s, determine

- a) the actual work output of the turbine [220 kJ/kg]
- b) the isentropic work output of the turbine [275 kJ/kg]
- c) the turbine adiabatic efficiency (η
_{T}) [80%] - d) the actual power output of the turbine [1000 kW]

*Derive* all equations
used starting from the basic energy equation for a flow system,
the equation of enthalpy for an ideal gas (Δh), the basic
definition of turbine adiabatic efficiency (η_{T}),
and the temperature/pressure relation for the isentropic process
of an ideal gas:

Use specific heat values for air at 800K (C_{P}=
1.099 [kJ/kg.K], k = 1.354)