Snecma Moteurs

Safran Ceramics

Herakles

Snecma Propulsion Solide

Snecma

Safran

Commissariat &#xc0; L'&#xc9;nergie Atomique Et Aux &#xc9;nergies Alternatives

Aircelle Limited

Safran Nacelles

Eric Conete

Didier Hippolyte Hernandez

Benoit Carrere

Alexandre Forestier

Georges Habarou

Eric Philippe

Mario Cesar De Sousa

Caroline Aumont

Pierre Camy

Thomas Revel

Laurent Baroumes

Matthieu Leyko

Pierre Jean-Baptiste Metge

Gw&eacute;na&euml;lle Calvez

Gautier Mecuson

Thomas Vandellos

Guy Bernard Vauchel

Patrick Gonidec

Eric Bouillon

Christophe Pieussergues

Jean-Philippe Joret

Guilhem Roux

Valérie Chaumat

Lisa Pin

Clément Marie Benoît Roussille

Mario César De Sousa

Vincent Devanlay

Philippe Bucci

Stephane Blanchard

Patrick Olivier Duchaine

Benjamin Lacombe

Guillaume Ruckert

Thierry Pancou

Benoît Carrere

Emmanuel Drevon

Ioannis Stasinopoulos

Francis Mirambeau

Beno&icirc;t Carrere

Fran&ccedil;ois Marie Paul Marlin

Renaud Barreteau

Amaury Benoit Jacques Paillard

An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.

Fastening of an exhaust cone in a turbomachine turbine

A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.

CMC materials with integrated thermocouple

A turbomachine turbine assembly having a longitudinal axis and including an exhaust casing, an ejection cone arranged downstream of the exhaust casing, the ejection cone having an outer annular wall for the flow of a primary air stream and an acoustic box arranged radially inside said outer annular wall. The acoustic box can include a radially inner annular wall and a connection member interposed longitudinally between the exhaust casing and the inner annular wall of the ejection cone. The connection member can be fastened to the exhaust casing and to the inner annular wall. The upstream end of the outer annular wall can be connected to the connection member with a degree of freedom in the radial direction and a degree of freedom in the longitudinal direction.

Turbomachine turbine assembly

A turbomachine subassembly including a first component forming a portion of a wall of a combustion chamber of the turbomachine and a second component forming a connecting member connecting the first component to a structural element of the combustion chamber, wherein the two components are made from materials having different coefficients of expansion, and wherein the two components are elements of revolution coaxial with a main axis A of the subassembly, and each including an annular radial wall, the radial walls facing one another and bearing against one another axially in a first direction, wherein the second component includes a plurality of clamping tabs, with the clamping tabs collaborating with the first component in order to produce an axial force causing the radial walls to bear against one another.

Subassembly comprising means for compensating for a difference in expansion

An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.

Acoustic attenuation structure made of composite material and method for manufacturing same

The invention relates to an assembly for an aircraft turbomachine, comprising a central element () for the ejection of gas, and a connecting flange () interposed between, upstream, a gas outlet () made of metal for a turbomachine, and, at the downstream end, the central element (). The connecting flange comprises an annular portion () and flexible tabs () having axially:

Ejection cone having a flexible aerodynamic attachment

A constant volume combustion system includes at least one combustion chamber having at least one admission port and an exhaust port. The system also includes at least one elastically deformable tongue made of ceramic matrix composite material forming an air admission valve, the tongue being present inside the chamber and being positioned facing the admission port, the tongue having a first end that is stationary relative to an inside wall of the chamber and a second end, opposite from the first end, the second end being free and movable relative to the inside wall.

Constant volume combustion system

An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.

Exhaust cone with flexible fitting

A constant-volume combustion system for a turbomachine includes a plurality of combustion chambers distributed in an annular manner about an axis defining an axial direction, each combustion chamber including an intake port and an exhaust port; a selective closure member rotationally movable about the axis with respect to the combustion chambers, the selective closure member including a ferrule facing the intake and exhaust ports of the combustion chambers, the ferrule containing at least one intake aperture intended to cooperate with the exhaust port of each chamber and at least one exhaust aperture intended to cooperate with the exhaust port of each chamber. Each intake aperture and each exhaust aperture are segmented by at least one segment extending in each aperture in the axial direction.

Constant-volume combustion system comprising a rotating closure element with segmented apertures

The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs.

Structure for fastening after-body parts of an aeroengine

A method of assembling together by brazing two parts made of composite material, each part having an assembly face for brazing with the assembly face of the other part, the method including: making a plurality of cavities in the assembly face of at least one of the two composite material parts, at least some of the cavities opening out into one or more portions of the part that are situated outside the assembly face; interposing capillary elements between the assembly faces of the composite material parts; placing a brazing composition in contact with a portion of the capillary elements; and applying heat treatment to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity between the assembly faces of the composite material parts.

Method for brazing parts made from a composite material, with anchoring of the brazed joint

A method of assembling together by brazing first and second parts made of composite material, each of the first and second parts having an assembly face for brazing with the assembly face of the other part, the method including making at least one perforation in the assembly face of the first part; interposing capillary elements between the assembly faces of the first and second parts made of composite material; placing the first and second parts facing each other while inserting a peg in each perforation of the first part; placing a brazing composition in contact with a portion of the capillary elements; and applying heat treatment to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity between the assembly faces of the composite material parts.

Method for the brazing of parts made from a composite material, incorporating a slug in the bond

An assembly comprising first and second parts made of composite material held one against the other by at least one fastener system comprising a bolt having a flat head from which there extends a threaded portion, and a nut having a flat head from which there extends a shank including tapping suitable for co-operating with the threaded portion of the bolt. The head of the bolt bears against a countersink formed in the first part. The head of the nut bears against a countersink formed in the second part. The fastener system is suitable, during axial expansion of the fastener system, for causing each head to tilt towards the countersink in which it is housed.

Assembly providing a connection that is self tightening with temperature

An aeroengine exhaust cone is arranged to extend from upstream to downstream along a longitudinal axis. The cone comprises a structural core of composite material made up of an axisymmetric part having an upstream endpiece at its upstream end and a downstream endpiece at its downstream end. The core provides structural strength to the cone. The cone has an acoustic attenuation system made of composite material and fastened on the structural core.

Exhaust with an acoustic attenuation system

An after-body assembly for an aeroengine, the assembly comprising an annular part () made of metallic material secured to the aeroengine and an after-body part () made of ceramic matrix composite material, the after-body part () being mounted on the annular part () by resiliently flexible fastener tabs () and having a first end () fastened to the annular part () and a second end () fastened to the upstream portion of the after-body part (). Each fastener tab () includes an axial abutment element () that extends radially from the second end () of the tab and having at least a portion thereof facing the first end (). The fastener tab () also includes a radial abutment element () at the second end () of the tab, the radial abutment element () at least partially overlying the first end ().

Flexible abutment links for attaching a part made of CMC

Growing community of inventors

Merignac, France

Eric Conete