Safran Aircraft Engines

Snecma

Jacques Marcel Arthur Bunel

Benjamin Frantz Karl Villenave

Gilles Ulryck

Mario Cesar De Sousa

Guillaume Sevi

Mario César De Sousa

Dan-Ranjiv Joory

William Louis Rodolphe Dousse

Alain Pierre Page

Nicolas Ovaere

Thomas Gricourt

Etienne Gérard Joseph Canelle

Sylvain Zambelli

Paul André Somazzi

Romain Nicolas Lunel

Emeric D'Herbigny

Dan Ranjiv Joory

Nicolas Christian Raymond Leblond

Pierre Tincelin

Pierrick Bernard Jean

Jacques André Michel Roche

Brice Arnaud Demoulin

Didier Hippolyte Hernandez

Denis Jean Maurice Sandelis

Christophe Pieussergues

Patrice Andre Commaret

Caroline Jacqueline Denise Berdou

Guy Vieillefond

Patrice André Commaret

Stephane Henri Guy Touchaud

Dominique Maurice Jacques Lains

Sandrine Gandelot

Bruno Giardini

Yann Vuillemenot

Yann Francois Jean-Claude Vuillemenot

Alain Paul Madec

Jacques Andre Michel Roche

Nicolas Pierre-Marie Girard

Faouzi Aliouat

Philippe Paul Marie Henry

Yann Francois Jean-Claude Vuillemont

Benjamin Villenave

Thierry Andre Emmanuel Cortes

Fabienne Vagner

Fabrice Dominguez

Jacques-A Roche

Bouzid Rabia

Frederic Ruellan

Emeric Christian Amaury D'Herbigny

Alexandre Eric Lefebvre

Frederic Marius Mathieu

Emeric D'herbigny

Didier Hyppolyte Hernandez

Frédéric Marius Mathieu

Yann François Jean-Claude Vuillemenot

Thierry André Emmanuel Cortes

Yann François Jean-Claude Vuillemont

Vagner Fabienne

A method for producing, by additive manufacturing, a part including at least one surface that must be held during the manufacturing, the method including: a step of forming a raw part by additive manufacturing, the raw part including a support including a pillar and a head which is an alveolar element connecting the pillar to the surface to be held; and a step of detaching the support from the rest of the raw part.

Optimization of supports for the additive manufacturing of a component

A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.

Fastening for a turbomachine combustion chamber

A turbomachine sealing ring has an axis of revolution and includes an annular support, an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector has a support sector, a coating sector, and a plate sector. Each plate sector ling includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.

Turbomachine sealing ring

A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.

Combustion chamber for a turbomachine

The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall () and a wall made of a refractory material (). A device () guides a spark plug () in said two orifices, the guiding device comprising a metal flange () and a floating ring (), the flange being shrunk onto or welded to the metal wall ().

Spark plug for a single-piece combustion chamber

A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.

Turbine engine combustion chamber

A method for obtaining, by additive manufacture, a component including at least one recess, this method including: a step of forming, by additive manufacture, a one-piece blank component, in which the at least one recess contains a support including a core in the form of a block of material and cellular elements that connect the core to the recess; and a step of detaching the support from the rest of the blank component in order to expose the recess.

Method and apparatus for optimisation of the supports for the additive manufacturing of a component with a recess

The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.

Guiding device in a combustion chamber

A bearing support for an aircraft engine, manufactured, in one piece, by powder-bed additive manufacturing from a manufacturing platform, including a cylindrical element including an annular stiffener with a cross-section that changes along its circumference, this stiffener being formed with alternating portions having a &#x393;-shaped cross-section, needing to be supported during the manufacture, and portions having a Y-shaped cross-section that are not supported during the manufacture.

Bearing support for an aircraft engine manufactured by additive manufacturing

A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.

One-piece combustion chamber

An assembly for a combustion chamber of a turbomachine. The assembly comprises an annular shell extending along a longitudinal axis, the shell having an inner wall intended to be turned towards a furnace of the combustion chamber and an outer wall opposite the inner wall and a projecting element extending radially from an area of the outer wall. The shell has at least one deflector projecting from the outer wall and located downstream of the projecting element with respect to a direction of gas flow along the outer wall, oriented along the longitudinal axis. The deflector extends circumferentially. Perforations are provided axially between the projecting element and the or each deflector.

Assembly for a turbomachine combustion chamber

A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.

Combustion chamber having a double chamber bottom

A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.

Production of a combustion chamber made of composite material

The thermal shrinkage of a casing () to regulate as best as possible the internal play between the rotor and the stator is carried out by a ring () fixed onto the skin () rather than by a circular ramp at a distance therefrom. The ring () comprises, between a collection box () and the skin (), a foraminous plate (), placed on an opening of the box () parallel to the skin () and at a short distance, in order to impose invariable and known ventilation conditions.

Device for cooling a turbomachine casing

A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.

Annular casting and shrink-fitted part of an aircraft turbine engine

Growing community of inventors

Thiais, France

Jacques Marcel Arthur Bunel