A jet engine with a large fan at the front, providing most thrust from bypass air
Turbofan
Ratio of air bypassing the engine core to air passing through it
Bypass Ratio
Large rotating airfoil at the front, accelerating bypass air
Fan
Raises air pressure before combustion (multi-stage)
Compressor
Chamber where fuel mixes with compressed air and ignites
Combustor
Exhaust duct that accelerates gases to produce thrust
Nozzle
Extracts energy from hot gases to drive the fan and compressor
Turbine
Aerodynamic casing housing the engine
Nacelle
Central part containing compressor, combustor, and turbine
Core
Annular passage for fan air that bypasses the core
Bypass Duct (Canal de dilution)
A rotating assembly (shaft + compressor + turbine stages)
Spool (Arbre)
Propulsive force generated by the engine
Thrust
Ratio of turbine discharge pressure to compressor inlet pressure
EPR (Engine Pressure Ratio) ; Rapport entre la pression refoulée par la turbine et la pression d’entrée du compresseur
Pressurized air tapped from compressor stages for aircraft systems
Bleed Air (Air de prélèvement)
Stationary airfoil rows that diffuse flow and guide it
Stator (Aubage fixe)
Rotating airfoil rows (in compressor or turbine)
Rotor (Aubage mobile)
Device injecting fuel into exhaust for extra thrust (mostly military)
Afterburner
Engine air intake (prise d’air du moteur) ; part of the nacelle
Inlet / OGA (Entrée d’air)
Overall measure of fuel burn vs. thrust produced
Efficiency (Rendement)
Mass of fuel burned per unit thrust per hour
SFC (Specific Fuel Consumption) ; Consommation spécifique
