Safran Aircraft Engines

Snecma

Snecma Moteurs

Kamel Benderradji

Alain Marc Lucien Bromann

Lilian Yann Dumas

Thomas Nolwenn Emmanuel Delahaye

Suzanne Madeleine Coustillas

Delphine Hermance Maxime Parent

Pamela Dominique Daniele Reichert

Marc R Marchi

David Audeon

Blaise Bergon

Liliana Gomes Pereira

Alain Marc Bromann

Laurent Jablonski

Arnaud Langlois

Vincent Roy

Pauline Anne Freche

Sandrine Hélène Quevreux

Joel Robert Mathieu

Pamela Dominique Danièle Reichert

Delphine Hermanee Maxime Parent

Alexandre Pierre François Leon

Pamela Dominique Reichert

A turbine engine assembly including a first rotor element and a second rotor element extending around a longitudinal axis X and coupled to one another by a gear coupling, the first rotor element including teeth and the second rotor element including complementary teeth which extend along the longitudinal axis and form the gear coupling. The first and second rotor elements each include a first and a second radial flange which are annular and arranged facing one another, and the assembly includes a sealing device configured to ensure that the gear coupling is sealed at the first and second flanges.

Turbine engine rotor element assembly equipped with a sealing device

An angular sector of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, includes, relative to the axis of said fixed blade ring, a radially outer platform, a radially inner platform, at least two blades extending between said platforms, and at least one block of abradable honeycomb material extending on the inside of the inner platform between transverse ends of the sector. The block of abradable material includes at least one transverse end wall shaped according to a toothed profile having at least one radially oriented tooth extending across an entire radial thickness of said block.

Angular sector for turbomachine blading with improved sealing

A holding device is used with a centripetal air sampling member of a rotor assembly that includes and downstream rotor discs and a centripetal air sampling member. The holding device has an annular support element with a housing configured to receive the air sampling member in a radial orientation, a first lateral extension, and a second lateral extension rigidly attached to the downstream rotor disc, extending substantially following the longitudinal axis and radially arranged externally with respect to the first extension. The holding device also includes a wedging ring axially arranged between a portion of the downstream rotor disc and the support element, the wedging ring being configured to simultaneously urge, under the action of a centrifugal force, the first extension in radial abutment against the second extension and the support element in radial abutment against a portion of the upstream rotor disc.

Device for holding a centripetal radial air sampling member

A ring for guiding variable-pitch blades and supporting an abradable coating for an aircraft turbomachine ring extends about an axis (X) and includes substantially radial orifices for mounting guiding sleeves intended each to receive a pivot of one of the blades. The ring may include a radially inner crown divided into sectors and supports the abradable coating. A radially outer annular ferrule may be divided into sectors and include the orifices for mounting the sleeves. In some embodiments, each ferrule sector is mounted about a crown sector by a circumferential sliding connection. The crown sector may include an immobilizer for rotationally immobilizing the sleeves of this ferrule sector about the axis.

Guiding ring for variable-pitch blades and method of mounting said ring

Variable-pitch blade control ring () for a turbine engine, including an annular body () configured to be mounted so as to be rotatable about an annular casing () of the turbine engine. The body links to levers () for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger () for axial abutment on at least one first surface () of the casing and for sliding on the surface.

Variable-pitch blade control ring for a turbomachine

The invention relates to a system for controlling variable-setting blades () for a turbine engine, which includes at least one control ring () mounted rotatably mobile about an annular casing () with axis of revolution A, at least one annular row of variable-setting blades () extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means () for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft () extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.

System for controlling variable-setting blades for a turbine engine

An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

Assembly for controlling variable pitch vanes in a turbine engine

The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot () that defines a substantially radial axis of rotation of the blade and which is connected by a lever () to control means (,) extending about said axis. The invention is characterized in that said control means include first links () supported by said pivots and second links () extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means ().

System for controlling variable pitch blades for a turbine engine

A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.

System for controlling variable-pitch vanes for a turbine engine

A cover of a centrifugal compressor intended to be rigidly connected to a turbomachine housing, which includes a plurality of ports, is provided. The cover further includes a fastening device for fastening the cover to the housing. A portion of the fastening device is located upstream relative to the ports and can be accessed by a fastening tool through at least one of the ports of the cover. A turbomachine uses this cover to form a sealed space, in particular with a view to collecting air.

Cover of a turbomachine centrifugal compressor capable of being rigidly connected via the downstream side near to the upstream edge of same, and turbomachine comprising this cover

The invention primarily relates to a turbomachine part () comprising a first upstream casing () and a second downstream casing (), assembled to one another using at least one flange () formed by an upstream flange part () of the first upstream casing () and a downstream flange part () of the second downstream casing (), the first upstream casing () and the second downstream casing () together at least partially delimiting the contour of an enclosure () in which at least one fluid (C) to be evacuated is contained, characterized in that it comprises a drainage device () comprising at least one drainage orifice () formed on the flange () connecting the first upstream casing () and second downstream casing (), in particular on the upstream flange part () of the flange (), allowing the discharge of said at least one fluid (C) outside the enclosure ().

Turbomachine part comprising a flange with a drainage device

A turbomachine compressor or turbine including annular anti-wear shims mounted against hooks of a stator, each shim being substantially of channel-section defining an annular groove for engaging on a hook, the shim mounted against the downstream hook bearing axially via its middle annular wall on the stator, or on the casing, and one of its side walls includes a bearing device at its end remote from the middle annular wall for bearing against the casing or the stator, respectively, which bearing device is elastically deformable in an axial direction so as to urge the stator upstream.

Annular anti-wear shim for a turbomachine

The present invention relates to a locking member () for a device for attaching ring sectors to an aircraft turbomachine casing, said member comprising two longitudinal clamping branches () extending rearward and connected at their rear ends by a transverse connecting branch (), their front ends being intended, between them, to press at least one ring sector () against at least one casing element (). According to the invention, the member () further comprises means () allowing it to be grasped, these means being arranged such that they project rearward from the transverse branch ().

Member for locking ring sectors onto a turbomachine casing, comprising means allowing it to be grasped

The gastight sealing device associated with a functional clearance existing between two sectors of a turbomachine includes an annular plate wound up on itself over at least one turn, covering functional clearance.

Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing device

A device for holding an annular end plate against a radial face of a rotor disc, the disc having in the radial face an annular recess behind a collar extending radially outwards, and the end plate having, in its radially inner part, an annular base bearing against the radially outer wall of the recess and a foot extending radially inwards in the recess from the base, the device including a split annular retaining ring disposed in the recess. The ring is constituted by a snap ring interposed axially between the foot of the end plate and the collar and the peripheral surface of which butts against the base, the peripheral surface and the collar comprising, when joined, notches, which open radially outwards and are intended to receive compression tools for the snap ring, which tools retract into the contour of the collar during the assembly or disassembly of the end plate.

Growing community of inventors

Moissy-Cramayel, France

Kamel Benderradji