Recovery of lubricating oil from a reduction gear of an aircraft turbine engine

Aircraft turbine engine (10), comprising:-at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V),-an annular exhaust casing (28) supporting at least one bearing (60, 62) for guiding the rotation of the first shaft and compri...

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Bibliographische Detailangaben
Hauptverfasser:	Chassagne, Amelie Argie Antoinette, Belmonte, Olivier, Levisse, Paul Ghislain Albert
Format:	Patent
Sprache:	eng
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 LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	Aircraft turbine engine (10), comprising:-at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V),-an annular exhaust casing (28) supporting at least one bearing (60, 62) for guiding the rotation of the first shaft and comprising arms (28a) located in the stream, downstream of the blades, and-a mechanical planetary gearbox (42) which comprises a sun gear (44), a ring gear (40) and a planet carrier (46), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device (70) for recovering and discharging oil projected centrifugally by the reduction gear.