**Problem 6.14 - 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)
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