Snecma

Safran Aircraft Engines

Safran Ceramics

David Locatelli

Didier Hippolyte Hernandez

Patrice Andre Commaret

Romain Nicolas Lunel

Antoine Robert Alain Brunet

Denis Jean Maurice Sandelis

Thomas Olivier Marie Noel

Clement Roussille

Clément Roussille

Didier Hernandez

Patrice Commaret

Antoine Robert Brunet

Daniel Quach

Sebastien Digard Brou De Cuissart

Sébastien Digard Brou De Cuissart

Jean-Louis Martial Verger

Jean-Christophe Leininger

Patrice André Commaret

Yvan Rappart

Ivan Herraiz

Patrick Audin

Benoit Georges Jocelyn Marie

Franck Edmond Maurice Truelle

Christelle Berthelemy

Claude Baldassari

Jean-Michel Serge Marcel Duret

Jean-Michel Duret

Benoît Georges Jocelyn Marie

Celine Yanxi Chan

Denis Sandelis

Céline Yanxi Chan

Thomas Noël

Thomas Olivier Noel

Denis Jean Sandelis

Benoit Georges Marie

A method for manufacturing a metal component using lost-wax casting is provided. The component is made of, for example, nickel alloy, with a columnar or monocrystalline structure with at least one cavity of elongate shape. The method includes creating a wax model of the component with a ceramic core corresponding to the cavity, creating a shell mold around the model, placing the mold in a furnace, with the base standing on the sole of the furnace, pouring molten alloy into the shell mold, solidifying the poured metal by gradual cooling from the sole in a direction of propagation.

Method for manufacturing a component using the lost-wax casting method with directed cooling

The invention relates to the field of casting, and more particularly to a method of producing a ceramic core () for casting, said core () presenting a shape that includes at least a first lateral protuberance (), and the method comprising at least a step of injecting a paste comprising a ceramic granulate and a polymer binder into a mold cavity In order to form a part () presenting a shape corresponding to the shape of the core () together with at least one additional lateral protuberance () adjacent to said first lateral protuberance (), a step of firing the part (), and a step of eliminating said additional lateral protuberance () from the part () after said firing step.

Method for producing a ceramic core

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 foundry method of casting monocrystalline metal parts, the method including at least casting a molten alloy into a cavity of a mold through at least one casting channel in the mold, subjecting the alloy to heat treatment, and removing the mold, and wherein the heat treatment is performed before an end of mold removal.

Method of casting monocrystalline metal parts

An annular combustion chamber for a turbomachine is disclosed. The chamber includes an inner wall, an outer wall, and a chamber end wall disposed between the inner and outer walls in the upstream region of the chamber. The chamber end wall presents an outer fastener rim and/or an inner fastener rim, and the outer and/or inner wall presents a respective upstream fastener rim. The chamber end wall and the outer and/or inner wall are fastened together via their fastener rims. Cooling channels are made between the fastener rims and open out to the inside of the combustion chamber. Advantageously, a spacer is placed between the fastener rims, and the channels are formed in the thickness or in the sides of the spacer.

Annular combustion chamber for a turbomachine

A deflector takes the form of a plate provided with a hole. The plate is a portion of a conical surface of revolution about a cone axis with a concave face and a convex face. The plate includes a contour with four sides. Two of these the sides are concentric circular arcs centered on the cone axis. The other two sides are segments of generatrices of the cone which connect the first sides. The invention is applicable to a deflector of a chamber endwall of a combustion chamber of a turbine engine.

Deflector for a combustion chamber endwall, combustion chamber equipped therewith and turbine engine comprising them

A welded assembly of combustion chamber elements is disclosed. Two subassemblies of the combustion chamber are fabricated by butt-welding, and a first subassembly has an intermediate connection ring welded thereto suitable for performing final welding with the second subassembly.

Method of fabricating a combustion chamber

An annular turbomachine combustion chamber comprising an inner wall, an outer wall, and a chamber end wall disposed between said inner and outer walls in the upstream region of said chamber, the chamber end wall presenting a central portion and an outer assembly flange, and the outer wall presenting an upstream assembly flange, the chamber end wall and the outer wall being assembled together by their assembly flanges, in which the free edge of said outer assembly flange is curved inwards. In addition, the outer face of the outer assembly flange presents a shoulder.

Annular turbomachine combustion chamber

A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstream side by an annular metal sheet. The sheet delimits, with the impeller of the compressor, a first annular passageway to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway to carry away a portion of the air flow coming out of the diffuser.

System for cooling the impeller of a centrifugal compressor

A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a centrifugal compressor, a diffuser, a combustion chamber, and an annular case arranged radially between the combustion chamber and a downstream end-piece of the diffuser. The annular case includes a radially external wall for the guidance of an air flow coming out of the diffuser, and a radially internal wall delimiting with the end-piece of the diffuser a channel for the air coming out of the diffuser to pass through.

System for ventilating a combustion chamber wall

A one-piece combustion chamber having an end wall subdivided into sectors. The combustion chamber comprises a chamber end wall interconnecting the inner and outer walls, and it includes windows closed by removable walls, each carrying a plurality of injector systems.

Annular combustion chamber with a removable end wall

A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a diffuser mounted at the inlet of the combustion chamber, an annular end-piece that extends downstream to an injection device for injecting ventilation air, and an annular convecting metal sheet being arranged radially between the combustion chamber and the end-piece of the diffuser in order to delimit, with an internal wall of the chamber, an annular stream for the flow of air that is stable and without separation supplying holes in the chamber and the injection device.

System for ventilating a combustion chamber wall in a turbomachine

An arrangement for a turbomachine combustion chamber is disclosed. The arrangement includes a chamber end wall pierced by at least one substantially circular opening, a deflector mounted from the downstream side of the chamber end wall in the opening by an annulus, an injector system associated with the opening and including an annular bowl that is flared downstream, passing through the opening, and a pinch ring that cooperates with the annulus to allow the injector system to shift off-center relative to the chamber end wall. The deflector includes an annular collar extending radially inwards. The bowl of the injector system includes at its downstream end an outwardly-open annular groove radially in alignment with the collar of the deflector in such a manner as to enable it to retract into said groove when the injector system shifts off-center relative to the chamber end wall.

Growing community of inventors

Gex, France

David Locatelli