enow.com Web Search

Search results

1. Results from the WOW.Com Content Network

2. 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.

3. 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]

4. Propelling nozzle - Wikipedia

   en.wikipedia.org/wiki/Propelling_nozzle

   A propelling nozzle is a nozzle that converts the internal energy of a working gas into propulsive force; it is the nozzle, which forms a jet, that separates a gas turbine, or gas generator, from a jet engine. Propelling nozzles accelerate the available gas to subsonic, transonic, or supersonic velocities depending on the power setting of the ...

5. Jet engine - Wikipedia

   en.wikipedia.org/wiki/Jet_engine

   A turbojet engine is a gas turbine engine that works by compressing air with an inlet and a compressor (axial, centrifugal, or both), mixing fuel with the compressed air, burning the mixture in the combustor, and then passing the hot, high pressure air through a turbine and a nozzle. The compressor is powered by the turbine, which extracts ...

6. Engine pressure ratio - Wikipedia

   en.wikipedia.org/wiki/Engine_pressure_ratio

   The engine pressure ratio (EPR) is the total pressure ratio across a jet engine, measured as the ratio of the total pressure at the exit of the propelling nozzle divided by the total pressure at the entry to the compressor. [1] Jet engines use either EPR or compressor/fan RPM as an indicator of thrust. [2]

7. Gas turbine engine thrust - Wikipedia

   en.wikipedia.org/wiki/Gas_turbine_engine_thrust

   If a turbojet engine has a purely convergent exhaust nozzle and the actual exhaust velocity reaches the speed of sound in air at the exhaust temperature and pressure, the exhaust gas cannot be further accelerated by the nozzle. In such a case, the exhaust gas retains a pressure which is higher than that of the ambient air.