Safran Aircraft Engines

Safran Helicopter Engines

Bertrand Guillaume Robin Pellaton

Sebastien Jean Laurent Prestel

Stéphane Pierre Guillaume Blanchard

Baptiste Marie Aubin Pierre Jouy

Laurent Claude Descamps

Youki Olivier Ito-Lardeau

Loic Villard

Olivier Pierre Descubes

Sébastien Jean Laurent Prestel

Adrien Moussette

Benoit Guillaume Silet

Jean-Luc Breining

Mathieu Cladiere

Josselin Luc Florent Sicard

Mathieu Laurent Herran

Lucas Benassis

Christophe Nicolas Henri Viguier

Thibaud Louis Zaia

Pierrick Raphael Americo Bauduin

Stephane Pierre Guillaume Blanchard

Gilles Marcel Jeannin

Benoît Guillaume Silet

Stéphane Raphaël Yves Richard

Gabriel Gorka Exilard

Nicolas Christophe Perra

Jerome Dinquel

Yohan Smith

Mathieu Pierre Cladiere

Loïc Villard

An assembly for a turbomachine includes at least one turbine having a turbine disc with an internal bore and an annular cavity which is arranged upstream of the disc. The assembly further includes a fire safety system with a cooling device that supplies the cavity with cooling air via injection means. The fire safety system includes means that divide the annular cavity into first and second cavities. A cooling air speed is maintained at the outlet of the injection means and the cooling air in the first cavity is guided to the internal bore of the turbine disc. A diffuser co-operates with the injection means and an annular cover co-operates with the diffuser and covers first attachment members arranged in the cavity. A radially outer surface of the cover at least partially guides the cooling air at the outlet of the diffuser.

Fire safety system for a turbomachine comprising means for maintaining a cooling air speed and corresponding turbomachine

A turbine for a turbomachine of longitudinal axis including an alternating arrangement of annular rows of movable blades and of fixed blades and a radially inner annular cavity formed radially inside the movable and fixed blades, and a supply circuit for supplying cooling air to the inner annular cavity, the downstream end of the supply circuit comprising an inner annular row of orifices and an outer annular row of orifices opening into the radially inner annular cavity. The turbine may also include means for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices.

Turbine

Disclosed is a movable vane () for a wheel () of an aircraft turbine engine, the vane () comprising a blade () delimited by an outer heel () comprising a first seal (), the vane () comprising an internal circuit () suitable for receiving a first minor gas flow (f), this circuit () comprising a supply cavity () opening at the root () via at least one inlet opening (), characterised in that the circuit () comprises at least two channels () connected with the supply cavity () and each opening on an outer surface of the first seal () via a discharge opening such that a gas jet (J) of the first minor gas flow (f) is capable of being discharged from each discharge opening, each channel () being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f) escaping between the heel () and a directly adjacent member ().

Movable vane for a wheel of a turbine engine

An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.

Assembly for turbine

A cooling device for an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

Device for cooling a turbomachine housing

A device for controlling the clearance between a rotor and a stator surrounding same, which is carried out by modifying the delivery flow carried in a rotor recess in order to provide a bleed flow that prevents the gases from the flow section from penetrating into the recess. A valve can partially close the delivery circuit, thus reducing the cooling of the rotor structure and allowing the expansion thereof and the reduction of the clearance with the stator, for certain operating speeds including cruise operating speeds. In addition, the delivery air is heated more at a lower flow rate, especially if it is made to follow a bypass provided with meanders in the hottest portions of the circuit.

Method and device for adjusting the clearance between a rotor and a concentric stator of an aircraft turbine engine

A labyrinth seal lip () comprises, standing on one of its lateral faces (), a deflector () which channels the flow of gas tangent to the lip () towards the facing seal () so as to disturb the leakage flow () through the gap and decrease the flow rate.

Labyrinth seal comprising a lip provided with a deflector

A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.

Turbo engine rotor disc

A tubular shaft () of a turbomachine, including at the inner periphery of same, a bath (), substantially perpendicular to splines (), the bath () includes cavities () distributed over a circumference centred on an axis of rotation (LL) of the shaft ().

Turbomachine shaft

The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (') configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set comprising a main ring () in which air circulates, the main ring () comprising orifices (&#x2032;) configured to spray a stream of air towards the turbine casing, the line set comprising a shield () configured to isolate the main ring () from a stream of air returning from the turbine casing towards the line sets after having been sprayed towards the turbine casing, the said shield () enveloping the main ring () and having orifices aligned with the orifices of the main ring ().

Device for ventilation of a turbomachine turbine casing

The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (), a hub (), hollow arms () connecting said collar () to said hub (), and an opening piece () which is located on the collar () and is suitable for being connected to an outlet tube () of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece () is attached onto the collar () and forms an extension of a hollow arm () such that an air flow () leaving the outlet tube () of the transient-operation valve penetrates the hollow arm () and flows into the hub ().

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Moissy-Cramayel, France

Bertrand Guillaume Robin Pellaton