MECHANICAL GEAR OF AN AIRCRAFT TURBINE ENGINE

• Main Authors: SIMON, Adrien, Louis, FOGLIA, Matthieu, Bruno, François
• Format: Patent
• Language: English; French; German
• Published: 25.08.2021
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; 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; MECHANICAL ENGINEERING; THERMAL INSULATION IN GENERAL; WEAPONS

A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.