Safran Aircraft Engines

Safran Transmission Systems

Safran Ventilation Systems

Amélie Argie Antoinette Chassagne

Olivier Belmonte

Paul Ghislain Albert Levisse

Antoine Robert Alain Brunet

Cédric Zaccardi

Michel Gilbert Roland Brault

Julien Fabien Patrick Becoulet

Jordane Emile André Peltier

Loïc Paul Yves Guillotel

Didier Jean-Louis Yvon

Antoine Jacques Marie Pennacino

Patrice Jocelyn Francis Gedin

Mohammed-Lamine Boutaleb

Clément Paul René Niepceron

Stéphane Petibon

Juan-Luis Marcos Izquierdo

Fabien Roger Gaston Caty

Clement Marcel Maurice Dejeu

Fabrice Joël Luc Chevillot

Vincent Christophe Brodbeck

Dimitri Daniel Gariel Marquie

Clément Marcel Maurice Dejeu

Dimitri Daniel Gariel Marquies

A turbomachine includes an enclosure lubrication and pressurization assembly having at least one lubricated enclosure protected by two seals. The turbomachine further includes a primary flow path surrounding the at least one lubricated enclosure, and in which circulates a primary flow passing through at least one compressor of the turbomachine. The assembly further includes an electric compressor supplied with air and connected to the at least one lubricated enclosure in order to introduce air under pressure into the enclosure through the seals.

Pressurization of a lubricated turbomachine enclosure

Disclosed is an aircraft turbine engine (), comprising a gas generator () and a fan () arranged upstream from the gas generator () and configured to generate a gas inlet stream (F), part of which flows into a duct of the gas generator to form a primary stream (), the turbine engine () comprising an electrical machine that is mounted coaxially downstream from the fan () and that comprises a rotor () surrounded by a stator () carried by an annular shroud (), this shroud () being surrounded by a casing () of the gas generator that defines, with this shroud (), a section of the flow duct for the primary stream (), stationary vanes () for straightening this primary stream () extending into this path.

Aircraft turbine engine equipped with an electrical machine

A heat exchanger between a fluid and an air flow, includes a heat exchange wall separating the fluid and the air flow, the heat exchange wall including a heat exchange surface that extends parallel to a longitudinal direction of the air flow and with which the air flow is in contact. The heat exchange wall includes at least one turbulence generator extending in a hollow manner in relation to the heat exchange surface.

Heat exchanger comprising a baffle wall with hollow turbulence generators

An oil recovery device for a reducer of an aircraft turbomachine, the device having a gutter extending around an axis and being intended to be arranged facing oil ejection means formed in a ring gear of the reducer of the turbomachine. The gutter can include at least one oil reception chamber which extends around the axis and which is open towards the axis so as to receive the oil coming from the oil ejection means. The reception chamber can be delimited by a first wall and a second wall arranged facing each other. The first wall can have an axial oil evacuation orifice and the second wall can have a radial dimension relative to the axis which increases increasingly along the axis towards the axial orifice, so as to allow oil ejected by the reducer to be conveyed to the axial orifice.

Oil recovery device for a turbomachine

Aircraft turbine engine (), comprising:—at least one first turbine rotor () connected to a first turbine shaft () and comprising rotor blades located in a stream (V),—an annular exhaust casing () supporting at least one bearing () for guiding the rotation of the first shaft and comprising arms () located in the stream, downstream of the blades, and—a mechanical planetary gearbox () which comprises a sun gear (), a ring gear () and a planet carrier (), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device () for recovering and discharging oil projected centrifugally by the reduction gear.

Recovery of lubricating oil from a reduction gear of an aircraft turbine engine

Disclosed is a turbomachine () with counter-rotating turbine for an aircraft, comprising: &#x2014;a high-pressure body, &#x2014;a low-pressure counter-rotating turbine (), &#x2014;a planetary-type mechanical epicyclic reduction gear (), &#x2014;a guide bearings (-) for the turbine shafts (), characterised in that said reduction gear () and certain of the bearings () are housed in a lubrication chamber () supplied with oil and comprising dynamic seals (-), and in that the turbomachine comprises circuits (C, C) for pressurising these seals.

Pressurising of lubrication chambers in a turbomachine with counter-rotating turbine

A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.

Turbomachine with counter-rotating turbine for an aircraft

An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Heat exchanger comprising an inter-vane wall provided with hollow turbulence generators

A turbomachine having a fan shaft supported by a first bearing positioned downstream of the fan, the first bearing including an outer ring attached to an annular support secured to the stator. The turbomachine includes at least one gas feed duct leading into an enclosure positioned against the disc, the gas feed duct being adapted to be fed at a second end with pressurized gas taken from an airstream of a high-pressure compressor of the turbomachine, so that the gas applies an axial force towards upstream on the disc during some operating phases of the turbomachine. The turbomachine further includes a ferrule imperviously sealing the enclosure.

Turbomachine with axial force recovery at the fan via pressurized gas feed

A guide vane for an aircraft turbomachine, the aerodynamic part of the vane being defined by an extrados body and an intrados body, the part comprising an internal lubricant cooling passage equipped with flow disturbing studs, including a first series of studs made in a single piece with the extrados body, and a second series of studs made in a single piece with the intrados body, the studs of the second series defining a second inter-stud space between them through which studs of the first series pass while the studs of the second series pass through the first inter-stud space. Furthermore, the end of the studs is located at a distance from the intrados body, and the end of the studs is located at a distance from the extrados body.

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Moissy-Cramayel, France

Amélie Argie Antoinette Chassagne