ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO

A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111)....

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Bibliographische Detailangaben
Hauptverfasser:	MALECKI, Robert E, SCHWARZ, Frederick M
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). A ratio of the distance to the diameter (Dt) is greater than or equal to about 0.90.