Snecma

Safran Aircraft Engines

Dominik Igel

Serge Rene Morreale

Yanis Benslama

Jeremy Dievart

Nelson Dos Santos

Adrien Jacques Philippe Fabre

Christophe Paul Jacquemard

Augustin Curlier

Serge René Morreale

Catherine Pikovsky

Gerard Philippe Gauthier

Maxime Aurélien Rotenberg

Delphine Leroux

Caroline Frantz

Nadege Hugon

Maxime Aurelien Rotenberg

Sarah Chartier

Daniel Bernava

Sébastien Tajan

Benissa Boujida

Jérémy Dievart

Boris Lemattre

Maxime Rotenberg

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 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

The invention relates to a turbine engine, comprising:

Cooling device for a turbomachine supplied by a discharge circuit

A turbomachine assembly including first and second bodies, in which one of the bodies is rotating relative to the other body around the axis of rotation of the turbomachine, is provided. A tight zone is formed between the bodies and includes a sealing gasket. A flowing fluid, in particular lubricant oil, is able to circulate inside the first and second bodies and to be driven toward the one rotating body from the other body. The one rotating body includes a device for guiding the rotation, in the direction of rotation of the one rotating body, of the flow of fluid inside the one rotating body so as to drive the flowing fluid away from the tight zone.

Turbomachine assembly comprising two bodies and means for guiding a fluid flowing from one body to the other

A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.

System for sealing an oil chamber from an adjoining exterior volume and turbo-machine provided with such a sealing system

A bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.

Bearing with lubrication means and system for changing the pitch of the blades of a turboprop propeller of an aircraft equipped with said bearing

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

The main purpose of the invention is a propeller () for a turbomachine () comprising a plurality of blades () and a blade support ring () fitted with housings () each of which holding a pivot () supporting the root () of one of said blades (), characterized in that at least one of the pivots () is associated with at least one dynamic scoop (), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.

Propeller comprising a moveable dynamic scoop

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

The invention concerns a system for providing a seal between two volumes (V, V) delimited by a part (A) mounted to rotate about an axis (A) and a stator (), said system (S) including an annular brush seal () that comprises:

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Hericy, France

Dominik Igel