Safran Aircraft Engines

Snecma

Christophe Scholtes

Antoine Robert Alain Brunet

Wilfried Lionel Schweblen

Thomas Nolwenn Emmanuel Delahaye

Ulysse Jacques Bernard Danteny

Morgan Balland

Hélène Mazet

Simon José Pierre Amoedo

Guillaume Claude Georges Philippe Linassier

Kevin Eugene Henri Giboudeaux

Hadrien Paul Alexandre Mage

Antoine Brunet

Simon Amodeo

Alexis Hector Ulysse George

Cedric Michel Claude Chretien

Simon Amoedo

Armel Marie Jean Pascal Touyeras

A variable-pitch stator vane for a turbine engine compressor stator, extending in a longitudinal radial plane including a radially inner plate and a radially outer plate between which at least one blade extends, each plate including a transverse longitudinal wall facing the other plate, characterised in that the transverse longitudinal wall of at least one plate includes at least one fin protruding radially towards the other plate.

Variable-pitch stator vane comprising aerodynamic fins

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 internal casing ferrule for a turbomachine, centered on a longitudinal central axis, which includes: a main body centered on this axis, with two ends, delimited by surfaces that are radially inner and outer relative to this axis; a thermal porous-structure insulation envelope having a volumetric porosity &#x2265;50%, which includes: a lateral portion entirely covering the two ends; when viewed in section transversely to this axis, exterior and interior portions entirely covering, respectively, the radially outer and inner surfaces of the main body; and a protective envelope which at least partially covers the envelope and which includes, when viewed in section transversely to this axis, radially outer and inner protective portions, respectively covering, at least in part, the exterior and interior portions.

Internal turbomachine casing having improved thermal insulation

An aircraft turbine-engine module casing including an external module casing and at least one sealing ring intended to surround a movable impeller of the module and arranged radially towards the inside with respect to the external casing. The casing includes at least one capillary heat pipe, a first end which is fixed to the sealing ring, and a second end which, opposite to the first, is fixed to a casing element arranged radially towards the outside with respect to the ring.

Aircraft turbine-engine module casing, comprising a heat pipe associated with a sealing ring surrounding a movable impeller of the module

The invention relates to a turbine engine extending longitudinally along an X axis and including a main duct in which an air stream flows, the turbine engine including at least one upstream compressor disc, at least one downstream compressor disc and a circuit for collecting air from an air stream collected in the main duct, the air collection circuit including a radial portion in which at least one air collection tube is mounted and a longitudinal portion extending between a cylindrical body and a central bore of the downstream compressor disc. The turbine engine includes a plurality of blades extending in the longitudinal portion of the air collection circuit, configured to be rotated about the X axis, in order to rotate the collected air stream.

Turbomachine comprising an air collection circuit

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

A vane for turbomachinery, such as, for example, an aircraft turbojet or turbofan engine, or an aircraft turboprop engine. The vane includes: (i) a first deicing fluid flow circuit inside the vane; (ii) a second deicing fluid flow circuit inside the vane; and (iii) a selector for directing the majority of the fluid towards the first circuit when the turbomachinery is in a first operating state, and for directing the majority of the fluid towards the second circuit when the turbomachinery is in a second operating state.

Vane for turbomachinery, such as an aircraft turbojet or turbofan engine or an aircraft turboprop engine

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 system in a cavity under the stator of a turbomachine flow path, the cavity being located between a root of a vane of the stator and a complementary rotor device, the root including two surfaces each provided with an abradable coating, the rotor device being provided with a first and a second sealing element, arranged facing the first and the second surface respectively, the first surface and the first sealing element forming a first sealing pair and delimiting a first leakage section between them, the second surface and the second sealing element forming a second sealing pair and delimiting a second leakage section between them, one of the two pairs tending towards a minimum leakage section when the other tends towards a maximum leakage section, and vice versa.

Growing community of inventors

Moissy-Cramayel, France

Christophe Scholtes