Snecma

Herakles

Stephane Pierre Guillaume Blanchard

Mathieu Dakowski

Romain Nicolas Lunel

Maurice Guy Judet

Thomas Daris

Clement Roussille

Thomas Langevin

Fabrice Garin

Yann Vuillemenot

Youki Olivier Ito-Lardeau

Dominique Coupe

Eric Bouillon

Julien Mateo

Fabrice Marcel Noel Garin

Laurent Bernard Cameriano

Alain Pierre Page

Patrick Joseph Marie Girard

Thierry Fachat

Guillaume Jean-Claude Robert Renon

Hubert Illand

Bertrand Pellaton

Laurent Pierre Joseph Ricou

Josselin Sicard

Helene Barret

Thibault Marie-Jacques Arnold

A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.

Rotating assembly for a turbomachine

A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.

Turbine wheel in a turbine engine

A rotor wheel for a gas turbine engine, the wheel including: a metal holder disk including a plurality of teeth at its periphery, the teeth extending radially outwards from the disk; a plurality of composite material blades, each blade including a root engaged between two adjacent teeth of the holder disk and that is held against the teeth by a pivot connection; a clamp disk including a plurality of teeth at its periphery extending in an axial direction, the clamp disk being fastened against the holder disk and on the same axis, with each of its teeth taking up a circumferential position between a blade root and a tooth of the holder disk; and a mechanism exerting a clamping force in a circumferential direction urging the teeth of the clamp disk against the blade roots.

Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping

A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

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

The invention provides a turbine machine rotor having blades of composite material, the rotor comprising an assembly disk, a plurality of composite material blades mounted on the assembly disk via their roots and each provided at its free end with a platform, and a metal shroud positioned on the blade platforms concentrically around the assembly disk and including labyrinth teeth that project radially outwards in order to abrade an abradable material carried by a casing surrounding the rotor, the casing being held stationary both axially and circumferentially relative to the blade platforms and being suitable for moving radially outwards in operation relative to the blade platforms.

Turbomachine rotor having blades of composite material provided with metal labyrinth teeth

A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.

Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly

A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that includes rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper. Additionally, final densification of the consolidated blade preform is performed in order to obtain a composite-material blade having an incorporated platform.

Method for producing a turbomachine blade made from a composite material

An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.

Cooling air bleed device in a turbomachine

Air bleed device for cooling components in a turbine engine, including an annular conduit () having a radially internal portion swept by an airflow () and which comprises at least one air inlet orifice () formed in an upstream radial wall () of the conduit (), a flap valve () for controlling the airflow entering through the orifice () and of which the flapper () includes a plate () applied against the wall () and capable of being moved by sliding on said wall () by a maneuvering member () mobile in translation parallel to the wall () between a position in which the plate () closes off the orifice () and a position in which the plate () opens said orifice.

Cooling air bleed device in a turbine engine

Device () for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct () having a radially internal wall () swept by a stream of air () and which comprises at least one air inlet orifice (), a flap valve () for controlling the flow rate of air entering through the orifice (), formed of an elastically deformable metal plate () of which a downstream end is fixed on an edge of the orifice (), and of which an upstream end can be displaced by a manoeuvring member () mobile in translation parallel to the axis () of the orifice between a position where the plate () seals this orifice and a position where the plate () opens this orifice.

Device for tapping cooling air in a turbomachine

A turbomachine rotor wheel having composite material blades is disclosed. The wheel includes a slideway disk having a circumferential groove at its outer periphery, the groove having an opening that is narrower than its bottom, with a plurality of composite material blades each having a blade root engaged in the groove of the slideway disk and presenting a longitudinal section adapted to the longitudinal section of the slideway disk in order to be held radially therein by co-operating shapes, and an orientation disk fastened coaxially around the slideway disk and including, in its outer periphery, a plurality of axial slots each of which is open at one end. Each slot presents a cross-section that is adapted to the cross-section of a corresponding blade root so as to hold it angularly by co-operating shapes.

Turbomachine rotor wheel having composite material blades

The present invention relates to a turbomachine rotor balancing system comprising a balancing flange () provided with through-passageways (), the system further comprising balance weights () each mounted fixedly on the flange () by means of a first and a second screw/nut assembly () having a first and a second screw () passing through a first and a second passageway (). According to the invention, said first screw is pressing against a first tangential end side () of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side () of the second through-passageway, and at a distance from the first tangential end side.

Balancing system for turbomachine rotor

A turbomachine rotor balancing system including a balancing flange provided with through-passageways, and balance weights mounted fixedly on the balancing flange by at least one screw/nut assembly passing through one of the passageways is disclosed. For each of the passageways, the flange has on its first face a first recess passing via the radial summit of the passageway. This first recess being deprived of contact with the screw head pressing on this first face. The flange has on its second face a second recess passing via the radial summit. The second recess being deprived of contact with the balance weight pressing on this second face.

A method for bonding a first part made of a composite to a second part to a predetermined dimension is disclosed. The method includes placing an insert into the first part, a first surface of the insert protruding beyond the predetermined dimension; machining the insert until the first surface is at the predetermined dimension; placing the second part on the insert; and fastening the second part via the insert. The use of an insert makes it possible to produce, with high precision, a reproducible assembly, which can still be dismantled.

Method of assembling two parts, at least one of which is made of a composite, and insert for carrying out the assembly

A device attaching an afterburner to a turbojet casing. The device comprises a transverse plate for attachment to the casing and at least two side brackets for supporting two legs of the afterburner. The brackets and the two legs extend longitudinally. The afterburner includes a flame-arrestor arm with the two legs.

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Chartrettes, France

Stephane Pierre Guillaume Blanchard