Lubricated enclosure for an aircraft turbine engine, limiting the retention of lubricant during pitching

A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lub...

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Bibliographische Detailangaben
1. Verfasser:	Serge Rene Morreale
Format:	Patent
Sprache:	eng
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 LUBRICATING 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 lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.