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2. Exhaust mixer - Wikipedia

   en.wikipedia.org/wiki/Exhaust_mixer

   Exhaust mixer of a JT8D engine of a Boeing 737-200. In aviation, an exhaust mixer / flow mixer is a feature of many turbofan engines, where slower, colder bypass air is mixed with faster, hotter core exhaust gases, before exhausting to atmospheric pressure through a common (mixed flow) propelling nozzle.

3. Components of jet engines - Wikipedia

   en.wikipedia.org/wiki/Components_of_jet_engines

   Exhaust or nozzle — Turbine exhaust gases pass through the propelling nozzle to produce a high velocity jet. The nozzle is usually convergent with a fixed flow area. Supersonic nozzle — For high nozzle pressure ratios (Nozzle Entry Pressure/Ambient Pressure) a convergent-divergent (de Laval) nozzle is used. The expansion to atmospheric ...

4. 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.

5. 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.

6. Airbreathing jet engine - Wikipedia

   en.wikipedia.org/wiki/Airbreathing_jet_engine

   Exhaust or Nozzle – Turbine exhaust gases pass through the propelling nozzle to produce a high velocity jet. The nozzle is usually convergent with a fixed flow area. Supersonic nozzle – For high nozzle pressure ratios (Nozzle Entry Pressure/Ambient Pressure) a convergent-divergent (de Laval) nozzle is used. The expansion to atmospheric ...

7. Pratt & Whitney JT9D - Wikipedia

   en.wikipedia.org/wiki/Pratt_&_Whitney_JT9D

   The engine featured a single-stage fan, a three-stage low-pressure compressor, and an eleven-stage high-pressure compressor coupled to a two-stage high-pressure turbine and four-stage low-pressure turbine. The JT9D-3, the earliest certified version of the engine, weighed 8,470 lb (3,840 kg) and produced 43,500 lbf (193 kN) thrust. [7]