BEARING ASSEMBLY FOR SUPPORTING A ROTOR SHAFT OF A GAS TURBINE ENGINE

In one aspect, a bearing assembly (100) for supporting a rotor shaft (106) relative to a support structure (108) of a gas turbine engine may generally include a bearing (112) including an outer race (116) and an inner race (114), an outer bearing housing (102) configured to extend radially between t...

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Bibliographische Detailangaben
Hauptverfasser:	MAHESH, SIVAKUMAR, VANAPALLI, VEERARAJU, MONDAL, BHASKAR NANDA, MILLER, JACOB PATRICK, KIRKENG, KEVIN L, CARTER, BRUCE ALAN, GANIGER, RAVINDRA SHANKAR
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BEARINGS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ELEMENTS OR CRANKSHAFT MECHANISMS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS 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 ROTARY BODIES OTHER THAN GEARING ELEMENTS SHAFTS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	In one aspect, a bearing assembly (100) for supporting a rotor shaft (106) relative to a support structure (108) of a gas turbine engine may generally include a bearing (112) including an outer race (116) and an inner race (114), an outer bearing housing (102) configured to extend radially between the outer race (116) of the bearing (112) and the support structure (108) of the gas turbine engine and an inner bearing support (104) configured to extend radially between the inner race (114) of the bearing (112) and the rotor shaft (106). In addition, the outer bearing housing (102) and the inner bearing support (104) each include at least one radially extending spring arm (138, 164) such that the outer bearing housing (102) and the inner bearing support (104) collectively form two springs coupled in series between the support structure (108) and the rotor shaft (106). Dans un aspect, le dispositif de palier (100) servant à supporter une tige de rotor (106) par rapport à une structure de support (108) dun moteur de turbine à gaz peut généralement comprendre un palier (112) comprenant une course externe (116) et une course interne (114), un logement de palier externe (102) configuré pour se prolonger radialement entre la course externe (116) du palier (112) et la structure de support (108) du moteur de turbine à gaz et un support de palier interne (104) configuré pour se prolonger radialement entre la course interne (114) du palier (112) et la tige de rotor (106). De plus, le logement de palier externe (102) et le support de palier interne (104) comportent chacun au moins un bras de ressort se prolongeant radialement (138, 164) de sorte que le logement de palier externe (102) et le support de palier interne (104) forment collectivement deux ressorts couplés en série entre la structure de support (108) et la tige de rotor (106).