Safran Aircraft Engines

Safran Transmission Systems

Olivier Formica

Olivier Belmonte

Julien Fabien Patrick Becoulet

Paul Ghislain Albert Levisse

Michel Gilbert Roland Brault

Gilles Alain Marie Charier

Caroline Marie Frantz

Nicolas Jerome Jean Tantot

Alexandre Jean-Marie Tan-Kim

Clément Paul René Niepceron

Patrice Jean-Marc Rosset

Fabrice Joel Luc Chevillot

Romain Truco

Julien Patrick Becoulet

Giles Alain Marie Charier

Fabrice Joël Luc Chevillot

Nicolas Jerôme Jean Tantot

A turbomachine fan module includes a fan shaft and a lubrication chamber traversed axially by at least part of the fan shaft. The module further includes at least one first bearing configured to support and guide the fan shaft in rotation. The fan shaft has a first tubular part closed by a cover, wherein the first tubular part has a distal end and a proximal end that are opposite each other along a longitudinal axis X and an annular squealer cavity, formed in an inner surface of the fan shaft, between the distal end and the proximal end. The cover has a body extending along the longitudinal axis X and mounted in the first tubular portion so as to cover and sealingly close the annular squealer cavity.

Fan module comprising improved sealing means for a lubricant chamber

An assembly for retaining a gear train in a turbomachine, the assembly comprising an annular casing () in which is engaged an annular part () rotatably locked in the casing () by annular means of cogging comprising first annular means of coupling formed on the annular part and co-operating with second annular means of coupling formed on the annular casing (), wherein a film of oil is formed in an annular space bounded between the first means of coupling and the second means of coupling.

Assembly for retaining a gear train in a turbomachine

An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

Fused soft and hard bearing rings

A turbomachine having a contrarotating turbine for an aircraft, the turbomachine including a contrarotating turbine of which a first rotor is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor configured to rotate in an opposite direction of rotation and connected to a second turbine shaft. The first rotor includes turbine wheels interleaved between turbine wheels of the second rotor, the turbomachine further including a planetary-type epicyclic mechanical reduction gear which has a sun gear driven in rotation by the second shaft, a ring gear driven in rotation by the first shaft, and a planet carrier attached to a first stator casing of the turbomachine located upstream of the contrarotating turbine with respect to a direction of flow of gas in the turbomachine. The turbomachine includes bearings for guiding the first and second shafts.

Turbomachine having a contrarotating turbine for an aircraft

A fan module including variable-pitch blades, a fan rotor bearing the blades of the fan, each mounted to pivot about a pitch axis; a fan shaft extending along a longitudinal axis X inside the fan rotor and driving the fan rotor in rotation. A power shaft drives the fan shaft with a planetary gear speed reducer At least a first and a second bearing guide the rotation of the fan rotor, housed inside a lubrication chamber. A system varies the pitch of the fan blades, including a connecting mechanism connected to the blades of the fan and a controller acting on the connecting mechanism. The first bearing is disposed upstream of the speed reducer and the second bearing is disposed downstream of the speed reducer. The fan rotor is connected to the fan shaft by an annular trunnion extending at least along an upstream portion of the lubrication chamber.

Fan module comprising variable-pitch blades

Aircraft turbomachine with mechanical reducer and counter-rotating turbine are described. The turbomachine includes a fan driven in rotation by a fan shaft, a mechanical reducer with epicyclic gear train, a gas generator comprising a counter-rotating turbine, a first turbine shaft of which is coupled to an input shaft of the reducer and to a pin, and a second turbine shaft of which is coupled to the fan shaft. The guidance of the reducer input shaft is provided by a first ball bearing, the guidance of the pin is provided by a second roller bearing, and the guidance of the first shaft is provided by a third roller bearing axially interposed between the first and second bearings.

Aircraft turbomachine with mechanical reducer and contrarotative turbine

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Moissy-Cramayel, France

Olivier Formica