GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER

A gas turbine engine (20) includes a fan section (22). A turbine section (28) is coupled to the fan section (22) via a geared architecture (48). The geared architecture (48) includes a torque frame (68) and a flex support (72) spaced apart from one another at a location. A gear train is supported by...

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Bibliographische Detailangaben
Hauptverfasser:	OTTO, John R, COFFIN, James B
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) includes a fan section (22). A turbine section (28) is coupled to the fan section (22) via a geared architecture (48). The geared architecture (48) includes a torque frame (68) and a flex support (72) spaced apart from one another at a location. A gear train is supported by the torque frame (68). A damper (78) is provided between the torque frame (68) and the flex support (72) at the location.