Total Energy At Nozzle Exit For a Turboprop Engine Calculator

In a turboprop engine, the nozzle exit refers to the exit of the gas turbine section, where the combustion gases pass through the power turbine before entering the propeller. The total energy at the nozzle exit is the sum of the enthalpy and kinetic energy of the exhaust gases.

The total energy ($E$) at the nozzle exit can be expressed as:

where,

• E is the Total Energy, i.e sum of kinetic and potential energy
• $h$ is the static enthalpy at the nozzle exit,
• $V$ is the velocity of the exhaust gases relative to the reference frame of the exhaust gases