Gas turbine bearing arrangement

A geared turbofan gas turbine engine includes a fan section (14) and a core section (12). The core section (12) includes a compressor section (16), a combustor section (18) and a turbine section (20). The fan section (14) includes a gearbox (62) and a fan (66). A low spool (34) includes a low turbin...

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Bibliographische Detailangaben
Hauptverfasser:	Merry, Brian D, Suciu, Gabriel L
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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A geared turbofan gas turbine engine includes a fan section (14) and a core section (12). The core section (12) includes a compressor section (16), a combustor section (18) and a turbine section (20). The fan section (14) includes a gearbox (62) and a fan (66). A low spool (34) includes a low turbine within the turbine section (20) and a forward connection to a gearbox (62) for driving the fan (66). The low spool (34) is supported for rotation about an axis at a forward most position by a forward roller bearing (50) and at an aft position by a thrust bearing (52).