Snecma

Snecma Moteurs

Herakles

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Safran Aircraft Engines

Jean-Luc Soupizon

Philippe Pabion

Sebastien Jean Laurent Prestel

Jean-Michel Guimbard

Philippe Jean-Pierre Pabion

Sebastien Alain Imbourg

Sebastien Jean Prestel

Claude Marcel Mons

Patrick Joseph Marie Girard

Gael Loro

Claude Gerard Rene Dejaune

Valerie Annie Gros

Godefroy Francis Frederic Drelon

Olivier Renon

Clement Roussille

Julien Mateo

Thierry Fachat

Paul Rodrigues

Sébastien Imbourg

Emmanuel Charrier

Serge Rene Morreale

Jacques Rene Bart

Georges Habarou

Serge René Morreale

Nicolas Eberling-Fux

Clément Roussille

Bruno Dambrine

Son Le Hong

Eric Roger Schwartz

Sébastien Jean Laurent Prestel

Nicolas Christian Triconnet

Jerome M Friedel

Xavier Firmin Camille Jean Lescure

Yannick Durand

Christian Rene Schnell

Jacques René Bart

Chantal Giot

Aurelien Rene-Pierre Massot

Patrice Rosset

Francois E Crozet

Jean-Michel Bernard Guimbard

Claude Gerard Dejaune

Patrick J Girard

Patrick Joseph Girard

Audrey Charrie

Ivan Herraiz

Jean-Bernard Vache

Sebastien Bourget

Aymeric Hugonie

Aurélien René-Pierre Massot

Florent Pierre Antoine Luneau

Patrick Rossi

Christophe Schultz

Damien Cordier

Patrick Didier Lestoille

Arthur Lou Nicolas Cohin

Claude Gérard René Dejaune

Philippe Gérard Marie Hazevis

Alain Allaria

Christian Ren)e Schnell

Christian René Schnell

Sébastien Bourget

Philippe Jean Pierre Pabion

Jean Bernard Vache

Sebastien Jean-Laurent Prestel

Henri Popinet

Sandrine Tourbier

Claude Bion

Charles Balleron

José Lopez

Xavier Lescure

Christophe Galand

Giot Chantal

Xavier Firmin Lescure

Philippe Jean Pabion

Godefroy Francis Drelon

Philippe Gerard Hazevis

Florent Pierre Luneau

Eric Schwartz

Gaël Loro

Valérie Annie Gros

Emmanuel B M Charrier

Philippe J-P Pabion

Godefroy Francis Frédéric Drelon

Jean-Pierre Pabion

Sébastien Alain Imbourg

Sébastien Prestel

Pabion Philippe Jean-Pierre Jean-Pierre

An air supply device for an aircraft engine turbine, in which device the air is conveyed to at least one aircraft engine turbine after being conveyed through at least one connecting sleeve from a low pressure distributor to a space defined by at least one upstream side and one downstream side, the upstream side having at least one opening and each pierced opening receiving one end of one of the connecting sleeves, wherein the upstream side and the downstream side are secured by at least one fastener. A retaining plate is used for each fastener in order to position a securing element of the fastener, the retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction.

Air supply device for aircraft engine turbines

A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element.

Turbine engine rotor including blade made of composite material and having an added root

A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.

Sealing device for a turbomachine turbine nozzle

An arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine, which includes an intermediary disc and a downstream disc of which the internal diameter and the axial position of the discs are defined in such a way that the tank is arranged inside the discs. The rotor supports a guide flange with an element of revolution of which the diameter of the section increases in the downstream direction, according to the direction of flow of the gases in the turbomachine. The downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and the upstream axial end of the flange is connected to the internal radial end of the intermediate disc.

Arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine

A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece.

Turbine engine turbine blade made of a ceramic-matrix composite with recesses made by machining

A vibration damper between outer platforms of adjacent composite-material blades of a rotor wheel of a turbine engine, the damper including a strip for inserting lengthwise in tangential cavities that are formed facing each other in the outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel.

Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel

The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction.

Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade

A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.

Nozzle for a turbomachine turbine

A device for axially retaining blades mounted on a turbomachine rotor disk is disclosed. The device includes a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also includes a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots. The retaining ring is housed in the groove of the disk, is held outwardly in the notches of the blade roots, and is constituted by a plurality of angular segments placed end to end.

Device for axially retaining blades mounted on a turbomachine rotor disk

An oil recovery device is disclosed. The oil recovery device includes two bearing supports mounted on an inter-turbine casing, a first bearing and a second bearing mounted on the bearing supports, a low-pressure turbine journal mounted rotating with respect to the inter-turbine casing, a fixed ferrule, and an oil passage provided in the low-pressure turbine journal making it possible to discharge the oil inside the fixed ferrule. The ferrule is preferentially widened from the end at which the oil is discharged.

Oil recovery device

Assembly of the connection of an arm to a ferrule is done by imbricating a side wing protruding from the end of the arm and keys bolted to the ferrule. The assembly may be supplemented with positioning pins.

Connecting radial arms to a circular ferrule by imbricating attached parts

The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure Pin the first enclosure is greater than the pressure Pin the second enclosure, and closed when P&#x3c;P

Gas turbine engine with valve for establishing communication between two enclosures

A cooled blade forming an upstream guide vane element for a turbomachine is disclosed. The airfoil includes a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in the first opening and a second end in the second opening, first spacers on the side of the first end, and second spacers on the side of the second end of the sleeve making a space between the outer face of the sleeve and the wall of the cavity. The blade is arranged so that the sleeve is inserted into the cavity through the first opening. The first spacers are secured to the sleeve and the second spacers are secured to the wall of the cavity of the airfoil. The invention makes it possible to mount the sleeve despite an accentuated curvature of the profile of the airfoil.

Cooled blade for a turbomachine

An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.

Inter-turbine casing with cooling circuit, and turbofan comprising it

The connection assembly of an arm to a sleeve is carried out substantially by parts of axes crossing the arm and the spacers between the parts of axes and the sleeve and the assembly bolts. The assembly and the disassembly are easy, even with highly reduced encumbrance, as the connection is light and devoid of high internal efforts, and a good position precision is obtained. The assembly may be applied to stators with an exterior sleeve and, an interior hub and radial link arms, which are encountered in certain turbomachines.

Connection of radial arms to a circular sleeve via axes and spacers

Growing community of inventors

Vaux Le Penil, France

Jean-Luc Soupizon