Safran Aircraft Engines

Baptiste Marie Aubin Pierre Jouy

Bertrand Guillaume Robin Pellaton

Sébastien Jean Laurent Prestel

Josselin Luc Florent Sicard

Mathieu Charles Jean Verdiere

Loïc Fabien François Villard

Adrien Moussette

Loic Villard

Sebastien Jean Laurent Prestel

Nicolas Contini

Youki Olivier Ito-Lardeau

Laurent Claude Descamps

Benoît Guillaume Silet

Vincent Dubois Dorogi

Gilles Marcel Jeannin

Arnaud Doublier

Loïc Villard

A cooling device () for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet () and one radially outer metal sheet () that are joined to one another and delimit, between them, cooling air circulation channels () extending circumferentially from a connection region (). Each channel () includes at least one air inlet and air ejection orifices (), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct () intended for the circulation of cooling air, the duct () located radially outside said metal sheets () and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (), the cooling duct () extending axially and arranged toward the circumferential end regions of the channels ().

Cooling device for a turbine of a turbomachine

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 sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.

Device for sealing between a rotor and a stator of a turbine engine

An abradable structure () is provided, with regions () with lower resistance to wearing produced by labyrinth seal lips (), at specific points in the axial direction of the turbomachine, where lip interference could cause the rotor to block up, such as after a temporary shutdown of the turbomachine. These regions may be produced by local weakening () or by the abradable material having a structure that is less dense. Application, for example, to turbomachine turbines.

Labyrinth seal abradable structure, notably for aircraft turbine

A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

Connecting assembly for cooling the turbine of a turbine engine

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 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

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 ().

Turbine engine exhaust casing with improved lifetime

A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.

Growing community of inventors

Moissy-Cramayel, France

Baptiste Marie Aubin Pierre Jouy