GEARED TURBOFAN

A gas turbine engine (20) comprises a fan rotor (62) having a hub (84) and a plurality of fan blades (82) extending radially outwardly of the hub (84). A compressor is positioned downstream of the fan rotor (62), and has a first compressor blade row defined along a rotational axis of the fan rotor (...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	SHERIDAN, William G, SCHWARZ, Frederick M
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (20) comprises a fan rotor (62) having a hub (84) and a plurality of fan blades (82) extending radially outwardly of the hub (84). A compressor is positioned downstream of the fan rotor (62), and has a first compressor blade row defined along a rotational axis of the fan rotor (62) and the compressor rotor (70). A gear reduction (87) is positioned axially between the first compressor blade row (91) and the fan rotor (62), and includes a ring gear (100) and a carrier (94). The carrier (94) has an axial length and the ring gear (100) has an outer diameter. A ratio of the axial length to the outer diameter may be greater than or equal to about 0.20 and less than or equal to about 0.40. The gear reduction (87) is connected to drive the hub (84) to rotate.