In a turboshaft engine, the nozzle exit typically refers to the exit of the gas turbine section, where the combustion gases pass through the power turbine before being used to drive a mechanical output, such as a helicopter rotor or industrial machinery.
The static enthalpy includes the internal energy, pressure energy, and potential energy of the gas at rest (i.e., static) just before entering the power turbine.
The total energy () at the nozzle exit can be expressed as:
where,
- E is the Total Energy, i.e sum of kinetic and potential energy
- is the static enthalpy at the nozzle exit,
- is the velocity of the exhaust gases relative to the reference frame of the exhaust gases