Snecma

Safran Aircraft Engines

Serge Rene Morreale

Gerard Philippe Gauthier

Laurent Gille

Dominik Igel

Arnaud Jean-Marie Pierrot

Yanis Benslama

Jeremy Dievart

Fabrice Chevillot

Jean-Luc Soupizon

Stephane Rousselin

Gilles Alain Marie Charier

Julien Fabien Patrick Becoulet

Gilles Alain Charier

Jacques Rene Bart

Catherine Pikovsky

Philippe Pierre Bouiller

Francois Jean Comin

Paco Maurer

Thomas Julien Roland Earith

Mathieu Jean Pierre Trohel

Stéphane Rousselin

Nelson Dos Santos

Nicolas Stoliaroff-Pepin

Jean-Yves Picart

Benoit Guillaume Farvacque

Albert Vial

Caroline Marie Franz

Herve Christian Denis Maine

Thomas Earith

Gérard Gauthier

Romain Lagarde

A scoop for an aircraft turbine engine, this scoop including a body which is movable between at least two positions, including a first position in which it is configured to capture part of a first air stream flowing in a first direction, wherein the body is movable into a second position in which it is configured to capture part of a second air stream flowing in a second direction which is opposite to the first direction, and wherein the body is mounted to move freely between the at least two positions so as to automatically adopt the first position when the first air stream flows, and to automatically adopt the second position when the second air stream flows.

Scoop for an aircraft turbine engine

Fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil-transfer device configured to transfer oil between a stator and a rotor. The device includes a stator ring having internal oil ducts, a shaft engaged in the ring and having internal oil ducts, and a plain bearing and rolling bearings which are mounted between the ring and the shaft, the ring including first fluidic-connection ports which are configured to cooperate by male-female engagement with ends of oil-supply sockets during blind assembly of the device by axial translation downstream of the device as a whole.

Fan module equipped with an oil-transfer device

A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.

Lubricated enclosure for an aircraft turbine engine, limiting the retention of lubricant during pitching

A rotary planet carrier for a mechanical reduction gear of a turbomachine having an annular row of tubular members for supporting bearings that are parallel to one another and to an axis of rotation (X) of the planet carrier. The tubular members include grooves for oil to flow through that are connected to oil ducts that extend from the grooves to an external peripheral surface. The grooves are rectilinear and parallel to one another and to an axis of revolution (Y) of an internal cylindrical surface of a corresponding tubular member. Some of the grooves have a width about the axis of revolution that is greater than the diameter of the ducts connected to this groove. Some of the ducts are connected to the corresponding groove that is closest to the axis of rotation (X) of the planet carrier.

Rotary planet carrier for a mechanical reduction gear of a turbomachine

The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor () having blades (), a stationary casing (), and a system for adjusting and controlling the pitch of the blades (), the rotor () including a central shaft () and a ring () for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor () housing said system, and the shaft () being guided by a first bearing () mounted in the stationary casing (), to the rear of the ring (), characterised in that the ring () is guided by at least one complementary bearing () located upstream of the first bearing ().

Fan module having variable-pitch blades for a turbine engine

The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor () carrying blades (), a stationary housing (), a mechanism () for regulating the pitch of the blades (), which is connected to the rotor, and a control means () mounted on the stationary housing () and comprising a control part () that can be moved in translation according to an axis (X) of rotation of the rotor (), and a bearing () for load transfer between the control part () and said mechanism, characterised in that it also comprises a stationary track () supporting the elastic restoring means () which are arranged so as to exert an axial restoring force on the control part () towards a determined position, preferably corresponding to the blade () feathering.

Fan module with variable-pitch blades for a turbomachine

An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover.

Assembly forming a gasket for a turbomachine, comprising a brush seal

A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured to regulate the flow of oil in the cooling circuit as a function of an oil temperature at output of the enclosure and a pressure difference at the level of the jet.

Regulation of the oil flow in a cooling circuit of a turbomachine

A device for sealing the coaxial shafts of a turbomachine includes an annular seal able to perform sealing by contact with the outer shaft, and a lubricating device to lubricate the region of contact between the annular seal and the outer shaft.

Device for sealing between the coaxial shafts of a turbomachine

A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.

Sealing device for an oil enclosure in a turbine engine bearing

A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.

Turbine engine comprising a floating bearing for guiding a shaft of the turbine engine

A turbine engine including a casing, a turbine engine shaft extending axially, a guide bearing for guiding the turbine engine shaft in the casing, the guide bearing including an inner circumferential ring rigidly connected to the turbine engine shaft, an outer circumferential ring fitted in a housing of the casing, and gripping rolling members, and a damping cavity configured to receive a damping fluid to form a damping fluid film for damping the guide bearing, the cavity being delimited radially between an outer surface of the outer ring and an inner surface of the housing. The outer surface of the outer ring and the inner surface of the housing are conical surfaces.

Turbo engine comprising a damping fluid film for damping a guide bearing of a shaft of the turbo engine and method of adjusting the thickness of such a damping fluid film

One of the components (), opposite a labyrinth seal (), is arranged sliding on a conical interface () of its support () and constructed from a material with different thermal expansions, so as to reduce the clearance with the component face to face (), at steady state, at high temperature. The sealing surface () may be assured by a circulation of oil.

Labyrinth seal and rotating machine comprising such a seal

A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor.

System for pressuring the bearing chambers of turbine engines machines using air taken from the intake duct

A fluidic dampening film supply method for a guiding bearing of a turbine engine shaft, said turbine engine being known to vibrate according to at least one given vibratory mode, said turbine engine being adapted to enter in resonance at a given resonance speed (w) for said given vibratory mode, a monitoring range (P) being defined around the resonance speed (w), a method wherein the fluidic dampening film of the guiding bearing being only supplied with fluid when the rotation speed of the turbine engine belongs to the monitoring range (P).

Growing community of inventors

Guignes, France

Serge Rene Morreale