Safran Aircraft Engines

Snecma

Safran Transmission Systems

Societe Nationale D'etude Et De Construction De Moteurs D'aviation-snecma

Serge René Morreale

Patrice Jocelyn Francis Gedin

Arnaud Jean-Marie Pierrot

Fabien Roger Gaston Caty

Michel Gilbert Roland Brault

Jean-Luc Soupizon

Adrien Louis Simon

Gilles Alain Marie Charier

Julien Fabien Patrick Becoulet

Gilles Alain Charier

Caroline Marie Frantz

Christophe Paul Jacquemard

Romain Guillaume Cuvillier

Olivier Renon

Romain Nicolas Lagarde

Yanis Benslama

Didier Gabriel Bertrand Desombre

Catherine Pikovsky

Dominik Igel

Laurent Gille

Sébastien Oriol

Matthieu Bruno François Foglia

François Jean Comin

Paco Maurer

Mathieu Jean Pierre Trohel

Jacques René Bart

Nicolas Stoliaroff-Pepin

Nelson Dos Santos

Benoit Guillaume Farvacque

Fabrice Chevillot

Jérémy Dievart

Marion Jeanne Pierrette Verdier

Antoine Pierre Albert Mariot

Albert Vial

Jean Marie Pierrot

Gérard Philippe Gauthier

Jean-Yves Picart

The invention relates to a turbomachine for an aircraft, comprising:

Aircraft turbomachine comprising a device for lubricating a bearing

A fan module for an aircraft turbine engine includes a fan with a fan shaft and variable-pitch fan blades. The fan module further includes an oil transfer device transfers oil between a stator and an actuator that controls the pitch of the fan blades the device includes a stator ring having an inner cylindrical surface and internal oil ducts, each of which opens onto the inner cylindrical surface. A shaft is engaged in the stator ring and rotates about an axis inside the ring. The shaft includes an outer cylindrical surface extending inside said inner cylindrical surface. The shaft has internal oil ducts, each of which opens onto said outer cylindrical surface A rolling bearing is mounted between the ring and the shaft, on each side of the plain bearing.

Fan module equipped with an oil transfer device

An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.

Arrangement for an aircraft turbine engine having improved lubrication, the arrangement comprising a shaft rotatably coupled to a following member by means of splines

A turbomachine includes a single ducted fan including a first shaft rotated by a second shaft via a speed reduction gearset, the second shaft being rotated by a third shaft of a turbine, the first shaft being guided in rotation with respect to a fixed structure via a first bearing and a second bearing placed upstream of the speed reduction gearset. The second shaft is guided in rotation with respect to the first shaft via a rolling bearing placed upstream of the speed reduction gearset, the rolling bearing comprising an outer ring housed in the first shaft, an inner ring connected to the second shaft and rolling elements arranged between the inner and outer rings.

Aircraft turbomachine with reducer

The invention concerns an assembly comprising an epicycloidal gear train () having a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the central pinion () surrounding and being rotationally fixed to a shaft () and the gear train comprising means for lubricating the teeth and axes () of the satellite pinions (), these means including an annular cup () fixed to the satellite carrier () opened radially inward. According to the invention, the assembly includes fixed oil spraying means () configured to spray oil towards oil deflecting means () towards the inside of the annular cup ().

Assembly comprising a planetary gearset

The invention concerns an epicycloidal gear train () comprising a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the gear train () comprising an annular cup () being integral with the satellite carrier () and open radially inward. According to the invention, the cup () is divided into a circumferential succession of first basins () of the first oil circuit and second basins () of the second oil circuit, the first basins () being fluidly separated from the second cells () and characterised in that the cup () comprises two annular walls () axially facing, the annular wall () of which is furthest from a median transverse plane () of the gear train () has openings () opening into the second basins ().

Planetary gearset

An oil distribution device for a rotating planet carrier of a step-down gear of a turbomachine is configured to be fixedly joined to a tubular member for supporting a bearing of the planet carrier, said oil distribution device having an oil inlet and a row of oil outlets at the external periphery thereof, said oil distribution device having at least two internal cavities which are connected in series by at least one calibrated port, one of these cavities, referred to as the receiving cavity, being connected to said oil inlet, and internal calibrated channels for conveying oil which extend substantially radially from said cavities as far as ports of the periphery of the device in order to form said oil outlets.

Oil distribution device for a rotating planet carrier of a mechanical reduction gear of a turbomachine

The invention concerns an epicycloidal gear train comprising a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the gear train () comprising means for lubricating the teeth and axes () of the satellite pinions (), these means including an annular cup () integral with the satellite carrier () opened radially inward. According to the invention, an annular bailer () is arranged radially inside the cup () and applied annularly sealingly to it, the annular bailer () being fixed in rotation to the central pinion ().

Lubrication for a planetary gearset

A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.

Fan module with variable-pitch blades for a turbine engine

The present disclosure describes a lubrication oil piping gutter of an aircraft turbomachine. The lubrication oil piping gutter can be used for a sun gear train reducer of the turbomachine. The gutter may include two lateral annular walls connected at their outer periphery by an annular bottom wall. In some embodiments, the annular bottom wall may include at least one oil evacuation opening in which is located a deflector configured to facilitate the flow of oil radially from the inside to the outside of the gutter.

Lubricating oil piping gutter of an aircraft turbomachine

An annular cap for collecting lubricating oil for turbomachine equipment is configured to extend around the equipment and to rotate about an axis. The cap includes through-orifices through which the oil can pass radially under the effect of spinning. The cap further includes means of deflecting the oil leaving the orifices in a direction substantially transverse to the axis and substantially tangential to the cap.

Lubricating-oil collection cap for turbomachine equipment

A system for measuring an oil retention volume of a first member of an engine lubricating system, the injected oil flowing inside the first member mixed with a first air volume, the mixture forming a first fluid, the measuring system including an oil injector at the inlet of the lubricating system; a first flowmeter to measure a first oil flow rate at the inlet of the lubricating system; a second flowmeter at the outlet of the first member to measure a second flow rate of the first fluid at the outlet of the first member; a measuring device to calculate a first value representing a quantity of oil in a volume of the first fluid flowing inside the first member; a calculator to calculate a third oil flow rate at the outlet from the second flow rate of the first fluid measured and the first value calculated and the instantaneous oil retention volume in the first member from the comparison of the first oil flow rate with the third oil flow rate.

System for measuring an oil retention volume in a lubricating system

A mechanical assembly includes two mechanical parts rotatable relative to each other. A first part is provided with a cylindrical cavity, a second part () has at least one cylindrical portion engaged in the cylindrical cavity of the first part, and a gap separates the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement in rotation between the first part and the second part (). A lubricant distribution network () is configured for feeding the gap with a fluid lubricant so as to form a fluid bearing. A first surface () selected from the inside surface of the cylindrical cavity of the first part and the outside surface of the cylindrical portion of the second part is provided with at least two lubricant admission orifices.

Plain self-centering bearing

A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.

Sealing device between two axisymmetric coaxial parts

An oil recovery device is disclosed. The oil recovery device includes two bearing supports mounted on an inter-turbine casing, a first bearing and a second bearing mounted on the bearing supports, a low-pressure turbine journal mounted rotating with respect to the inter-turbine casing, a fixed ferrule, and an oil passage provided in the low-pressure turbine journal making it possible to discharge the oil inside the fixed ferrule. The ferrule is preferentially widened from the end at which the oil is discharged.

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Moissy-Cramayel, France

Serge René Morreale