Aircraft turbine engine with reduction gear

The geared fan 2 of a turbine engine comprises a first shalt 5 driven in rotation via a reduction gear 6 and guided in rotation with respect to a support 14 of a fixed structure 8 via an upstream bearing 15 and a downstream bearing 16. The downstream bearing 16 guides the first shaft 5 with respect...

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Bibliographische Detailangaben
Hauptverfasser:	Michel Gilbert Roland Brault, Julien Fabien Patrick Becoulet, Xavier Jean Yves Alain Agneray
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GEARING 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 STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	The geared fan 2 of a turbine engine comprises a first shalt 5 driven in rotation via a reduction gear 6 and guided in rotation with respect to a support 14 of a fixed structure 8 via an upstream bearing 15 and a downstream bearing 16. The downstream bearing 16 guides the first shaft 5 with respect to a downstream branch 18 of the support 14, the first shaft 5 and the support 14 together defining an enclosure 19. The reduction gear 6 comprises a ring gear 20 fixed to the structure 8 via a shell 21. The lubrication means comprises at least one pipe 22 for conveying a liquid lubricant (oil), the pipe 22 being located in the enclosure 19 and passing through an orifice 23 made in the shell 21 and an opening 24 made in the downstream branch 18.