Safran Aircraft Engines

Safran Ceramics

Safran Helicopter Engines

Sébastien Serge Francis Congratel

Lucien Henri Jacques Quennehen

Nicolas Paul Tableau

Clément Jean Pierre Duffau

Clément Jarrossay

Antoine Claude Michel Etienne Danis

Matthieu Arnaud Gimat

Aurélien Gaillard

Clément Emile André Cazin

Patrice Eneau

Pierre Jean-Baptiste Metge

Charlotte Marie Dujol

Pascal Cédric Tabarin

Gilles Gérard Claude Lepretre

Patrick Joseph Marie Girard

David René Pierre Le Cair

Arthur De Castro

Maurice Guy Judet

Erwan Daniel Botrel

Nicolas Xavier Trappier

Fabrice Marcel Noel Garin

Didier René André Escure

Léandre Ostino

Baptiste Dorian Lawniczek

Michel Slusarz

Célia Iglesias Cano

Philippe Picot

Matthieu Simon

Hubert Jean-Yves Illand

Patrice Jean-Marc Rosset

Antoine Hubert Marie Jean Masson

Denis Daniel Jean Boisseleau

Pascal Cedric Tabarin

Simon Parinet

Fabrice Marcel Noël Garin

Clement Marie Benoit Roussille

A bladed assembly () includes two adjacent blades (). Each blade () a platform () located at a free radial end. The platform () of the first blade () includes a lateral face () which is located circumferentially opposite an associated lateral face () of the platform () of the second blade (). The platform () of the second blade () comes into contact with the platform () of the second blade () only via an excrescence () which projects circumferentially with respect to the lateral face () of the platform () of the first blade () in the direction of the platform () of the second blade (), and the excrescence () is received in a groove () formed in the platform () of the second blade.

Turbomachine blading assembly comprising means for limiting vibration between platforms

Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Turbine blade of a turbine engine with self-generated interlock contact force in operation

Turbine shroud assembly comprising sections () made from CMC and forming a shroud () and a support structure (), each section having a base () with a radially internal face () and a radially external face (), from which there extend in a projecting manner an upstream attachment lug () and a downstream attachment lug (), the support structure comprising a collar (), from which there radially extend in a projecting manner towards the shroud an upstream radial flange () and a downstream radial flange (), by which the lugs of each section of the shroud are retained, the shroud () being retained by axial pins () which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.

Turbine shroud assembly

A turbomachine part of an annular assembly includes a structural body and a connecting edge integral with the structural body. Each connecting edge includes at least one groove intended to receive a sealing tab. Each connecting edge is made of composite material including a fibrous reinforcement consisting of randomly-oriented short fibres, the reinforcement being densified by a ceramic matrix.

Turbomachine part with connecting edge made of composite material with ceramic matrix and short fibres and method for the manufacture of same

A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

Guide vanes assembly with position-maintaining device

A turbine including a casing and a nozzle including an outer metallic shroud secured to the casing, an inner metallic shroud, and a plurality of nozzle segments made of CMC forming a crown extending between the outer shroud and the inner shroud, each segment including a strut, an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut, wherein for

Turbomachine turbine having a CMC nozzle with load absorption and positional adjustment

A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

Turbomachine stator assembly comprising an inner shroud having upstream and downstream portions assembled by axial translation

A turbine ring assembly extending around a longitudinal axis and comprises:

Turbine ring assembly

A turbine vane of a turbine engine such as a turboprop or a turbojet, the vane comprising a root supporting a blade, the vane including at least one air-circulation duct for cooling the air during operation, the duct including, at the vane root, an inlet portion for collecting the cooling air, the inlet portion extending away from a lower surface of the vane root opposite the blade. At least one inlet portion is provided with a helical element for rotating the cooling air in order to improve the cooling efficiency thereof.

Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air

A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.

Turbine nozzle having blading made of ceramic matrix composite through which a metal ventilation circuit passes

A turbine comprises a casing, an outer metal shroud, an inner metal shroud and an annular distributor having a plurality of CMC ring sectors, each sector comprising a mast, an inner platform, an outer platform and at least one blade having a hollow profile that defines an inner housing, the inner and outer platforms each having an opening communicating with said inner housing, and the mast passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder projecting axially towards the outside of the mast configured to radially cooperate with a first shoulder and radially press the blade against the mast.

Turbomachine turbine having a CMC nozzle with load spreading

A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.

Aircraft turbine shroud cooling device

A distribution element intended to be fixed to a support structure for supplying cooling fluid to a wall to be cooled facing the distribution element, the distribution element including a body defining a cooling fluid distribution internal volume and a multi-perforated plate which delimits the internal volume and includes a plurality of outlet through-perforations which put the cooling fluid distribution internal volume into communication with the wall to be cooled, the distribution element including an inlet orifice opening into the cooling fluid distribution internal volume, wherein for directing the cooling fluid from the inlet orifice to the plurality of outlet through-perforations the cooling fluid distribution internal volume includes directional fins.

Element for distributing a cooling fluid and associated turbine ring assembly

The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

Assembly of a turbomachine turbine ring and stator

A turbine shroud sector made of ceramic matrix composite, of longitudinal axis X and which includes a base with a radially internal face, a radially external face from which there extend upstream and downstream tabs for attachment to a shroud support structure. The base includes a first slot and a second slot, which is arranged radially on the outside of the first slot. The slots are formed in the lateral face. A first and a second sealing strip rest against a radially internal wall of the first and second slots. The first strip has the overall shape of an omega and the shroud sector exhibits a first clearance which is defined radially between a central part of the first strip and the radially internal wall of the first slot, and a second clearance which is defined radially between this central part and a radially external wall of the first slot.

Growing community of inventors

Moissy-Cramayel, France

Sébastien Serge Francis Congratel