Snecma

Safran Aircraft Engines

Aircelle Limited

Adrien Jacques Philippe Fabre

Christophe Paul Jacquemard

Sébastien Emile Philippe Tajan

Adrien Laurenceau

Vivien Mickaël Courtier

Sebastien Tajan

Adrien Louis Nicolas Laurenceau

Laurent Jablonski

Michel Andre Bouru

Régis Eugène Henri Servant

Christophe Marcel Lucien Perdrigeon

Pierre Jean-Baptiste Metge

Jean-Noel Mahieu

Paul Antoine Foresto

David Marsal

Romain Boudier

Dominique Gerhardt Mayhew

Charles-Henri Michel Marie Derrez

Sarah Chartier

Damien Daniel Sylvain Lourit

Stéphane Ibarzo

Gilles Alain Marie Charier

Matthieu Arnaud Gimat

Philippe Gérard Edmond Joly

Jean-Marc Claude Perrollaz

Jonathan Evert Vlastuin

Clément Cottet

Dominik Igel

Cedric Zaccardi

Eric Jacques Boston

Eddy Keomorakott Souryavongsa

Sebastien Emile Philippe Tajan

Alain Paul Madec

Michel André Bouru

Laurence Francine Vion

Cyril Roger Yves Le Pecheur

Daniel Bernard Dao

Michel Rognant

Dimitri Daniel Gabriel Marquie

Jean-Noël Mahieu

Sébastien Tajan

Dominique Gerhadt Mayhew

Frédéric Patard

Sebastien Marcelino Juste

David Khalil Charrier

Nicolas Horn

Regis Eugéne Henri Servant

Matthieu Gimat

Fibrous preform for a composite blade and also a composite blade formed by means of such a preform, a rotor and a rotating machine comprising such a blade, the preform comprising a first longitudinal section, configured to form a blade root, and a second longitudinal section, extending from the first longitudinal section, configured to form a portion of an airfoil, wherein the first longitudinal section has a first thickness at its upper end and wherein the second longitudinal section comprises at least one set-back zone having a thickness at least three times less than the first thickness, said set-back zone occupying at least 50% of the second longitudinal section.

Preform for a composite blade

A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.

Separation nozzle for aeronautic turbomachine

A bearing support designed to be secured to a stationary turbojet element for supporting a journal, including a cone which widens from a central portion for supporting the journal to a portion for securing to the stationary element, a cylindrical body extending the portion for securing to the stationary element while surrounding the cone, an upstream skirt carried by the cone for defining an upstream enclosure for the central portion, and at least one downstream revolution element carried by the cone for defining a downstream enclosure for the central portion. The bearing support can be made as a single part produced by additive manufacturing.

Turbojet bearing support produced by additive manufacturing

An aviation turbine engine having at least one unducted rotary propeller having a plurality of blades, each blade including: a blade body made of composite material including fiber reinforcement densified by a matrix, the fiber reinforcement of the blade body presenting three-dimensional weaving, the body extending between a leading edge and a trailing edge, and a protective fitting for protecting the leading edge and made of composite material having fiber reinforcement densified by a matrix, the fitting being adhesively bonded onto the leading edge of the blade body, the fitting being formed from a dry fiber preform injection molded with a densifying resin, and a polyurethane film for providing protection against erosion covering the blade body and the fitting.

Aircraft turbomachine provided with an unducted propeller with blades having a composite-material insert bonded to their leading edges

The invention relates to a bellcrank for a turbomachine having a first bore, a second bore and a third bore, the first bore being connected to the second bore by a first branch, the second bore being connected to the third bore by a second branch, the third bore being connected to the first bore by a third branch, a fourth branch connecting the first branch to the second branch.

Bellcrank for a turbomachine

A vane includes a fiber reinforcement having a three-dimensional weaving densified by a matrix, the fiber reinforcement including in a single woven part a root portion and an airfoil portion extending along a longitudinal direction between the root portion and a vane tip portion and along a transverse direction between a leading edge portion and a trailing edge portion. The airfoil portion includes first and second extrados and intrados faces. The fiber reinforcement includes a non-interlinking forming a housing inside the fiber reinforcement, a conformation part being present in the housing. The non-interlinking extends over a non-interlinked area inside the airfoil portion of the fiber reinforcement included between the root portion and the vane tip portion in the longitudinal direction and between the leading edge portion and the trailing edge portion in the transverse direction, the non-interlinking also opening outside the airfoil portion of the fiber reinforcement.

Composite propeller vane or blade for aircraft integrating a conformation part

A guide vane located in a fan air flow in an aircraft twin-spool turbomachine, the vane being made with an extrados body and an intrados body between which there is a thermal conduction matrix. Furthermore, the attachment devices between the two spools are arranged outside the aerodynamic part of the vane.

Outlet guide vane for turbomachine, made from several parts assembled together by attachment means outside the flow stream

The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes () located radially outside the nacelle in order to be traversed by a secondary jet () flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (), each vane () comprising a blade extending from a root that is used to removably attach same to a base of the associated support (). Each base () is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base () and the vane root supported by the base () is surrounded and covered by a detachable aerodynamic cover ().

Unducted-fan aircraft engine including a propeller comprising vanes with roots outside the nacelle and covered by detachable covers

A controller for controlling a system for changing the pitch of blades of a turbine engine propeller, the controller includes a fixed member () and a member () which is movable in translation along a longitudinal axis (X) relative to the fixed member (), and an anti-rotation device () configured so as to prevent the rotation of the movable member () relative to the fixed member () about the axis (X). The anti-rotation device includes a longitudinal structural crossmember () which is mounted by a first and a second end () on the fixed member, and support and guide unit () integrally in translation the movable member along the axis (X), the crossmember extending radially outside the movable member and the fixed member relative to a radial axis (Y) which is perpendicular to the axis (X) and being guided through the support and guide unit.

Means for controlling a pitch change system comprising an anti-rotation device, a pitch change system equipped with said control means, and a corresponding turbine engine

The invention relates to turbine engine module () including a case () rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case () comprising a cylindrical wall () extending between an inner wall () and an outer wall () of the rotating case (), and a system () for changing the pitch of the blades () of the propeller. The wall () is connected downstream to a first frustoconical wall () and upstream to a second frustoconical wall (), a first rolling bearing () being inserted respectively downstream directly between a radially outer face () of the inner wall () and a radially inner face () of the first frustoconical wall, and a second rolling bearing (') inserted downstream directly between the radially outer face () of the inner wall () and an inner face () of the second frustoconical wall ().

Pitch change module for turbine engine and corresponding turbine engine

A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis.

Pitch change system equipped with means for supplying fluid to a control means and corresponding turbine engine

An aircraft propeller blade including a streamlined structure constituted by at least one piece of fiber reinforcement obtained by three-dimensionally weaving yarns and densified by a matrix, together with a spar including an enlarged portion extending outside the fiber reinforcement and forming the root of the blade, and a shaping portion present in a housing arranged inside the fiber reinforcement. The fiber reinforcement includes a non-interlinked zone forming the housing inside the fiber reinforcement. The non-interlinked zone opens out into the bottom portion and into the rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement. The opening present in the rear edge of the fiber reinforcement extends over a height that is less than the height of the housing.

Composite propeller blade for an aircraft

The invention relates to a device () for a non-streamlined propeller () with blades () having variable pitch of a turbomachine (), the device comprising a support () intended to support a blade () and including a cylindrical foot (), a bearing comprising a radially internal annular section () and a radially external annular section () capable of pivoting with respect to each other, the foot () being mounted in said internal section () of the bearing. The device comprises a hub () mounted in the foot (), said hub () including a rim () comprising a face () coming to bear on the radially internal annular section () of the bearing, the hub () and the foot () of the support () comprising complementary engagement elements () interacting with a locking component ().

Device for fixing blades with variable pitch of a non-streamlined turbomachine propeller

An unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.

Unducted fan for an aircraft turbine engine

The present invention relates to a rotor for a turbomotor impeller, with variable-pitch blades, comprising blade roots capable of rotating in a blade supporting structure and a device for feathering the blades. Said feathering device comprises at least one flyweight secured to a crank connected by a gear set to at least one of said blade roots.

Turbomachine impellor rotor with device for feathering the blades of the impellor

Growing community of inventors

Montrouge, France

Adrien Jacques Philippe Fabre