Safran Aircraft Engines

Snecma

Snecma Moteurs

Antoine Robert Alain Brunet

Christophe Scholtes

Jean-Christophe Leininger

Thierry Argaud

Laurent Jablonski

Cédric Zaccardi

David Locatelli

Amélie Argie Antoinette Chassagne

Sebastien Juste

Julien Sedlak

Didier Hippolyte Hernandez

Romain Nicolas Lunel

Daniel Georges Plona

Patrice Andre Commaret

Dominique Raulin

Vincent Paul Gabriel Perrot

Damien Joseph Cellier

Wilfried Lionel Schweblen

Olivier Stephane Domercq

Patrick Claude Pasquis

Eric Pierre Georges Lemarechal

Delphine Leroux

Morgan Balland

Emmanuel Houradou

Patrice André Commaret

Gilles Yves Aouizerate

Hélène Mazet

Kevin Eugene Henri Giboudeaux

Teddy Frederic Gilbert Chantrait

Vincent Gilbert Alex Wagner

Mael Thevenot

Jean-Yves Fernand Paris

Gilles Jean-Luc Dessein

Alexis Hector Ulysse George

Philippe Avignon

Frederic Renault

Alexandre Franck Arnaud Chartoire

Claude Chomel

David Joseph Serlan

Guillaume Claude Georges Philippe Linassier

Simon Amodeo

Mickael Dias Gomes

Hadrien Paul Alexandre Mage

Simon Amoedo

Sébastien Juste

Laurent Jablonsky

A heat exchanger between a fluid and an air flow, includes a heat exchange wall separating the fluid and the air flow, the heat exchange wall including a heat exchange surface that extends parallel to a longitudinal direction of the air flow and with which the air flow is in contact. The heat exchange wall includes at least one turbulence generator extending in a hollow manner in relation to the heat exchange surface.

Heat exchanger comprising a baffle wall with hollow turbulence generators

A sealing assembly () for a turbine engine comprising a first element () and a second element (), the first and second elements () being concentric and in relative rotational movement with respect to each other about an axis of rotation (X), the sealing assembly () comprising at least one first wiper () and an abradable member (), the first wiper () being annular in shape and carried by the first element (), the first wiper () extending radially towards the abradable member () and continuously around the axis of rotation (X), the abradable member () being annular in shape and carried by the second element (), the abradable member () extending tangentially opposite the first wiper (), the first wiper () comprising primary angular portions (), each extending tangentially along a primary angular sector ('), the primary angular portions () each having, in cross-section, a first constant profile, characterised in that the first wiper () comprises secondary angular portions () each extending tangentially along a secondary angular sector (′), the secondary angular portions () each having, in cross-section, a second profile different from the first profile, the number of secondary angular portions () being equal to the number of primary angular portions (), the secondary angular portions () being interposed between the primary angular portions ().

Sealing assembly for a turbine engine

An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Heat exchanger comprising an inter-vane wall provided with hollow turbulence generators

The invention relates to an assembly for a turbomachine, comprising a stator () and a rotor () rotatable relative to the stator () about an axis, the rotor () comprising blades each &#xd7;comprising a vane () connected to a radially inner platform (), a block of abradable material () extending radially inwardly from the radially inner platform () the stator () having a shroud comprising an annular area (), at least one lug () extending radially outwardly from said annular area (), the radially outer end of the lug () cooperating with the block of abradable material ().

Assembly for a turbomachine

An abradable element () for a turbomachine comprises a body () formed from an abradable material and extending between a wear face () and a bottom (). The body comprises blind cavities () opening up into the wear face and filled in with a material with a colour different from the colour of the material forming the body of the element () to form wear indicators of the wear face () of the element ().

Abradable turbomachine element provided with visual wear indicators

Assembly forming a labyrinth seal for a turbomachine, comprising: at least one abradable material of which the inner surface defines a stair shape with a sequence of treads and risers; a plurality of fins extending radially toward said inner surface, the fins each comprising, at least in part, an upstream side wall forming a riser facing the corresponding fin such that, when seen in axial cross-section, the tangent at the top of the upstream side wall of at least one fin and the straight line passing through the downstream side wall of said at least one abradable material intersect, the angle between said tangent and said straight line being strictly between 5 and 15&#xb0;.

Assembly forming a labyrinth seal for a turbomachine comprising an abradable material and inclined fins

A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90&#xb0; with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2&#x2264;J/D&#x2264;0.6 where D is the hydraulic diameter of an injection orifice.

Device for deicing a splitter nose and inlet guide vanes of an aviation turbine engine

An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

Anti-icing system for a turbine engine vane

The main object of the invention is an angular stator sector () for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal () forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Angular stator sector for a turbomachine compressor comprising a brush seal

A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Compressor shroud comprising a sealing element provided with a structure for entraining and diverting discharge air

A sealing device for an enclosure of a turbine engine formed by an assembly of juxtaposed rotating and/or static bodies is provided. The sealing device includes at least one brush seal having a brush body, carried by at least one first member, and bristles extending from the brush body and arranged so as to rub against at least one second member rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment. The device further includes a labyrinth-type seal, the labyrinth being positioned in series with the brush seal between the inside of the enclosure and its outer environment.

Sealing of turbine engine enclosures produced by brush seal and labyrinth

A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved.

Casing for a moving-blade wheel of turbomachine

A system for ventilating a downstream cavity of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least one annular deflector mounted in this cavity in order to oppose the rise of hot air along the downstream face of the impeller and in order to cause the diverted hot air to be driven by the air taken from the outlet of the compressor.

Ventilation of a downstream cavity of an impeller of a centrifugal compressor

A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360&#xb0; around the axis of the compressor.

Device for bleeding air from a turbomachine compressor

The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (), an inner casing () and at least one shock absorbing ring () connecting the casings, the module also comprising an annular cavity () on the downstream side of the ring (), with a passage () formed in it through which an airflow () is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (), downstream from it, this device comprising at least one coat of thermal insulation (), and at least partly delimiting the annular cavity () on the downstream side of it ().

Turbomachine module provided with a device to improve radial clearances

Growing community of inventors

Moissy Cramayel, France

Antoine Robert Alain Brunet