Safran Aircraft Engines

Snecma

Alain Marc Lucien Bromann

Kamel Benderradji

Lilian Yann Dumas

Suzanne Madeleine Coustillas

Pamela Dominique Daniele Reichert

Thomas Nolwenn Emmanuel Delahaye

Blaise Bergon

Delphine Hermance Maxime Parent

Liliana Gomes Pereira

Olivier Belmonte

Thierry Georges Paul Papin

Francois Marie Paul Marlin

Pierre Debeneix

Clementine Charlotte Marie Mouton

Aude Abadie

Erick Jacques Boston

Frederic Paul Eichstadt

Jeremy Phorla Lao

Fabrice Cretin

Damien Lourit

Arnaud Langlois

Vincent Roy

Yvan Guezel

Alain Piot

Pamela Dominique Danièle Reichert

Alexandre Pierre François Leon

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

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 device for guiding variable pitch diffuser vanes of a turbine engine is provided. The device includes a first ring having an axial portion at its periphery that is extended by a collar extending radially outwards; a second ring mounted around the axial portion of the first ring so as to cooperate therewith to define a plurality of outwardly open sockets; a plurality of cylindrical bushings, each mounted in a respective socket for the purpose of receiving a guide pivot of a diffuser vane; and a resilient clamping ring for cooperating with one of the rings in order to clamp the two rings axially one against the other.

Device for guiding variable pitch diffuser vanes of a turbine engine

This invention relates to an assembly () for an aircraft turbofan comprising a flowpath splitter () downstream from which there is firstly a fan flowpath () inner delimitation ring () and secondly a compressor case (), the assembly comprising a plurality of outlet guide vanes () provided with an inner platform () located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part () to support the delimitation ring (), comprising a radially outer end () fixed to a downstream part of this ring () and a radially inner end () fixed to the compressor case ().

Aircraft turbofan comprising an intermediate ring with simplified downstream support

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 invention relates to a device for adjusting the centring of a turbo-engine pivoting vane control ring, comprising a control ring () centred on a longitudinal axis (X-X) of the turbo-engine and provided with a plurality of tapped holes () running in a radial direction and a plurality of pad holders (), each comprising a threaded rod () screwed into one of the ring's tapped holes (), each pad holder () holding, at an inner end, a pad () intended to come into contact with a cylindrical shell (), coaxial with the ring. The control ring () comprises, in addition, a plurality of slots () running in a tangential direction, each slot () communicating with one of the ring's tapped holes () The device comprises means () of pinching, in a longitudinal direction, each of the slots () in such a way as to lock the pad holders () in position.

Device for adjusting the centring of a turbo-engine pivoting vane control synchronization ring

A gas turbine engine includes at least one compressor stage with an inner ring under variable angle stator vanes including axial keys for centering the inner ring with respect to the stator vanes, and including at least one sealing member support mounted on the inner ring. The keys include a transverse groove cooperating with a radial rib arranged transverse to the engine axis on the periphery of the support for the sealing member.

Retaining of centering keys for rings under variable angle stator vanes in a gas turbine engine

A device for rotationally blocking a retaining ring () on a rotor disk () includes successive first () and second () blocking hooks of the disk (), at least one cleat () of the retaining ring () arranged close to a split () in the ring (). The position of the at least one cleat () on the retaining ring () is such that, when the retaining ring () is in place in a groove () situated in the rotor disk (), the at least one cleat () is in abutment against the first blocking hook (), and the split () is covered by the second blocking hook ().

Growing community of inventors

Moissy-Cramayel, France

Alain Marc Lucien Bromann