A text only version of this slide is available which gives all of the flow equations. The interactive Java applet EngineSim is also available. This program solves these equations and displays the thrust and fuel flow values for a variety of turbine engines. Most modern passenger and military aircraft are powered by gas turbine engines, which are also called jet engines. There are several different types of jet engines, but all jet engines have some parts in common.
All jet engines have a nozzle which produces the thrust as described on the thrust equation slide.
The nozzle also sets the total mass flow rate through the engine as described on a separate slide. The nozzle sits downstream of the power turbine and, while the nozzle does no work on the flow, there are some important design features of the nozzle. Tt8 divided by Tt5 is 1.0 as shown on the slide. The static pressure at the exit of the nozzle is equal to free stream static pressure, unless the exiting flow is expanded to supersonic conditions. Considering the energy equation for the nozzle, the specific total enthalpy is equal to the static enthalpy plus the square of the exit velocity divided by two.