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2. Propelling nozzle - Wikipedia

   en.wikipedia.org/wiki/Propelling_nozzle

   A nozzle operates according to the Venturi effect to bring the exhaust gasses to ambient pressure, while forming them into a propulsive jet; if the pressure upstream of the nozzle is high enough, the flow will reach sonic speed . The role of the nozzle in back-pressuring the engine is explained below.

3. Pratt & Whitney F119 - Wikipedia

   en.wikipedia.org/wiki/Pratt_&_Whitney_F119

   The rectangular convergent-divergent nozzle is fully variable for both the convergent throat and divergent areas for high nozzle pressure ratio and can vector ±20° in the pitch axis, greatly improving the aircraft's pitch authority by augmenting the pitching moment of the tail with engine thrust; this enables the F-22 to remain controllable ...

4. Components of jet engines - Wikipedia

   en.wikipedia.org/wiki/Components_of_jet_engines

   The propelling nozzle converts a gas turbine or gas generator into a jet engine. Power available in the gas turbine exhaust is converted into a high speed propelling jet by the nozzle. The power is defined by typical gauge pressure and temperature values for a turbojet of 20 psi (140 kPa) and 1,000 °F (538 °C). [18]

5. Pratt & Whitney F100 - Wikipedia

   en.wikipedia.org/wiki/Pratt_&_Whitney_F100

   The F-15 ACTIVE showing its 3D axisymmetric thrust vectoring nozzles on its F100-PW-229s. A variant of the -229 fitted with a 3-dimensional axisymmetric thrust vectoring nozzle, referred by Pratt & Whitney as the Pitch/Yaw Balance Beam Nozzle (P/YBBN), was tested on the F-15 ACTIVE (Advanced Control Technology for Integrated Vehicles) in the ...

6. Turbine map - Wikipedia

   en.wikipedia.org/wiki/Turbine_map

   Typical primary nozzle map. The following discussion relates to the expansion system of a 2 spool, high bypass ratio, unmixed, turbofan. On the RHS is a typical primary (i.e. hot) nozzle map (or characteristic). Its appearance is similar to that of a turbine map, but it lacks any (rotational) speed lines.

7. Turbojet - Wikipedia

   en.wikipedia.org/wiki/Turbojet

   The nozzle pressure ratio on a turbojet is high enough at higher thrust settings to cause the nozzle to choke. If, however, a convergent-divergent de Laval nozzle is fitted, the divergent (increasing flow area) section allows the gases to reach supersonic velocity within the divergent section.