The total energy at the nozzle inlet for a turboshaft engine involves considering the enthalpy and kinetic energy of the incoming air before combustion. Turboshaft engines are a type of gas turbine engine commonly used to power helicopters and other rotorcraft.
This formula combines the static enthalpy, which represents the energy content of the incoming air due to its temperature and pressure, and the kinetic energy, which represents the energy associated with the motion of the incoming air.
To use this formula, you would need specific values for the static enthalpy and the velocity of the incoming air. These values depend on the ambient conditions and the design of the engine, and they are typically provided in the engine specifications.
The total energy () at the nozzle Inlet can be expressed as:
where,
- E is the Total Energy, i.e sum of kinetic and potential energy
- Â is the Static Enthalpy at nozzle Inlet,
- Â is the velocity of the incoming air relative to the reference frame of the engine.