RESILIENT BEARING MOUNT WITH INTEGRAL DAMPER FLUID PASSAGE FOR A GEARED TURBOFAN ENGINE

A gas turbine engine (20) includes a bearing support ring (68) with a first annular body (124) and a second annular body (130) disposed radially inward of the first annular body (124). A radial spring (136) is connected to the first annular body (124) and the second annular body (130). The gas turbi...

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Bibliographische Detailangaben
1. Verfasser:	DiBENEDETTO, Enzo
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BEARINGS BLASTING ELEMENTS OR CRANKSHAFT MECHANISMS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ROTARY BODIES OTHER THAN GEARING ELEMENTS SHAFTS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a bearing support ring (68) with a first annular body (124) and a second annular body (130) disposed radially inward of the first annular body (124). A radial spring (136) is connected to the first annular body (124) and the second annular body (130). The gas turbine engine (20) includes a frame (57) with a case (94) that extends around the first annular body (124). The frame (57) includes an annular member (96) connected to the case (94) and positioned radially between the radial spring (136) and the second annular body (130). A fluid port (98) extends radially through the annular member (96). A seal (70) is disposed around the annular member (96) and forward of the fluid port (98). A first fluid passage (146) extends through the case (94). A second fluid passage (148) is formed between the bearing support ring (68) and the frame (57) and extends from the first fluid passage (146) to the fluid port (98). A bearing outer race (102) is disposed inward of the second annular body (130).