Snecma

Herakles

Safran Aircraft Engines

Safran Ceramics

Clement Roussille

Dominique Coupe

Gael Evain

Guillaume Renon

Jean-Luc Soupizon

Antoine Jean-Philippe Beaujard

Stephane Pierre Guillaume Blanchard

Nicolas Eberling-Fux

Julien Mateo

Patrick Joseph Marie Girard

Elric Georges André Fremont

David Marsal

Stephane Blanchard

Romain Nunez

Ivan Herraiz

Pierre-Louis Alexandre Carlos

Mathieu Louis Jean Leduc

Lucien Quennehen

Adele Lyprendi

Jonathan Goering

Romain Nicolas Lunel

Eric Bouillon

David Locatelli

Fabrice Marcel Noel Garin

Son Le Hong

Thierry Fachat

Nicolas Christian Triconnet

Thierry Tesson

Aline Planckeel

Hubert Illand

Sylvain Yves Jean Duval

Claire Groleau

Bruno Andre Jean Varin

Alain Allaria

Alain Schweitzer

Gilles Ansorena

Stephane Pierre Blanchard

Nicolas Otin

Jeremy Blachier

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. The ring support structure includes two annular flanges between which the attachment portion of each ring sector is held. Each annular flange of the ring support structure presents at least one sloping portion bearing against the attachment portions of the ring sectors, the sloping portion, when observed in meridian section, forming a non-zero angle relative to the radial direction and relative to the axial direction.

Turbine ring assembly

The invention concerns a rotary assembly for a turbomachine, comprising a disk of which the outer periphery is formed from an alternation of cavities and teeth (), and blades extending radially from the disk and of which the roots () are engaged axially and held radially in the cavities of the disk. According to the invention, the teeth of the disk and the blade roots comprise, at the upstream and/or downstream axial ends of same, axial shoulders () disposed circumferentially end-to-end in alternation and together forming a cylindrical surface () facing radially towards the inside of the disk.

Rotary assembly for a turbomachine

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having first and second annular flanges, each ring sector having first and second tabs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. Each of the first and second tabs of the ring sectors has an annular groove. Each of the first and second annular flanges of the ring support structure has an annular projection received respectively in the annular groove of the first tab or in the annular groove of the second tab of each ring sector. A resilient element is interposed between the annular projection of the first flange and the annular grooves of the first tabs, and also between the annular projection of the second flange and the annular grooves of the second tabs.

Turbine ring assembly supported by flanges

A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.

Method of optimizing the profile of a composite material blade for rotor wheel of a turbine engine, and a blade having a compensated tang

The invention concerns a rotary assembly for a turbomachine, comprising: According to the invention, the sealing means comprise radially an internal annular part () and an external annular part () structurally separate from each other, and the facing radial ends of which are adapted for a relative radial movements by sliding sealingly, only an absorption of the centrifugal forces of the external part () being provided rotationally by the platforms ().

A rotor disk blade for a turbine engine, the blade being made of composite material including fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a portion constituting an airfoil and a blade root forming a single piece, the blade root having two substantially plane opposite lateral flanks that are formed respectively extending the pressure side surface and the suction side surface of the airfoil. The blade root is clamped between two metal plates fastened against the lateral flanks of the blade root by a bolt and a nut passing through the plates and the blade root. The bolt has a head bearing against one of the two plates. The nut has a head bearing against the other plate.

Rotor disk blade with friction-held root, rotor disk, turbomachine and associated assembly method

A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element.

Turbine engine rotor including blade made of composite material and having an added root

A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Turbine engine blade made of composite material, and a method of fabricating it

A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same

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

A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece.

Turbine engine turbine blade made of a ceramic-matrix composite with recesses made by machining

A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material.

Layout of a blisk

A method for fabricating a turbomachine blade or vane of composite material including fiber reinforcement densified by a matrix is disclosed. The method includes: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.

Composite material turbomachine engine blade or vane, compressor stator segment or turbine nozzle segment incorporating such vanes and method for manufacturing same

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

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Bordeaux, France

Clement Roussille