Safran Aircraft Engines

Snecma

Terreal

Snecma Société Anonyme

Olivier Renon

Patrick Sultana

Nicolas Pommier

Patrick Jean Laurent Sultana

Laurent Cédric Zamai

Jean-Luc Soupizon

Yannick Durand

Florence Irène Noëlle Leutard

Boucif Bensalah

Julien Fabien Patrick Becoulet

Alain Dominique Gendraud

Mario Cesar De Sousa

Guillaume Sevi

Sebastien Jean Laurent Prestel

Serge René Morreale

Maxime Didier Delabriere

Stéphane Pierre Guillaume Blanchard

Guilhem Seize

Francois Robert Bellabal

Arnaud Lasantha Genilier

Simon Nicolas Morliere

Frederic Noel

Sébastien Jean Laurent Prestel

Nicolas Jean-Marc Marcel Beauquin

Eddy Stephane Joel Fontanel

Paul Rodrigues

Mario César De Sousa

Sylvain Yves Jean Duval

Jean-Michel Boiteux

Christian Rene Schnell

Matthieu Fiack

Giuliana Elisa Rossi

Eddy Stéphane Joël Fontanel

Clément Charles Jérémy Coiffier

Stephane Nicolas Piron

Mathieu Bissardon

Mathieu Delalandre

Benoit Argémiro Matthieu Debray

Lore Marie Ricquemaque

Thomas Gérard Daniel Riviere

Pierrick Raphael Americo Bauduin

Thibault Jamon

Soufien Akachkachy

Abdelkader Benyahia

Alberto Martin Matos

François Robert Bellabal

Christian Ren)e Schnell

Sebastien Jean-Laurent Prestel

Gilles Gérard Lhuillery

Christian René Schnell

Helene Orsi

Philippe Rembry

Eddy Stephane Fontanel

Florence Irene Leutard

Pierrick Raphael Bauduin

Maxime Delabriere

Thomas Gerard Riviere

Hélène Orsi

Maxime DELABRIÈRE

Frédéric Noel

Christophe Fabre

Romain Blavet

A casing for a turbomachine includes an internal hub, an external flange coaxial with the internal hub, arms extending radially from the internal hub to the external flange, each arm having a wall, two or more wire harnesses that connect a first electrical apparatus, which is arranged radially outside the external flange, and a second electrical apparatus, which is arranged radially inside the internal hub, a sheath extending within an arm at a distance from the wall of the arm, the sheath including an internal face defining an internal cavity that receives the two or more wire harnesses, and one or more shims mounted in the sheath and holding the wire harnesses at a distance from an internal face of the sheath and holding the wire harnesses at a distance from one another within the sheath.

Auxiliary arm for a turbomachine exhaust casing

A turbine includes a first rotor and a second rotor that can rotate in opposite directions and are interleaved. The turbine further includes a ring to which abradable material is secured, the ring, unsegmented, extending between the first impellers of the first rotor and the second rotor, over a sector of between 350 and 360°, and, axially between an upstream end and a downstream end of the ring, the ring is held with the second rotor.

Gas turbine for twin-rotor aircraft

The invention relates to a turbomachine for an aircraft, comprising:

Aircraft turbomachine comprising a device for lubricating a bearing

The invention relates to an assembly () for a turbomachine turbine comprising a casing () including an annular wall () extending about an axis, and means of cooling the casing (), the said means of cooling comprising a collector housing () and at least one tube () extending circumferentially around the annular wall () of the casing () and connected to the housing (), with the tube () comprising cooling-air ejection orifices.

Assembly for a turbomachine turbine

A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.

Method for manufacturing a turbine engine part and the thereby produced part

Counter-rotating turbine (C) of a turbomachine () extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading () is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum () on which an outer movable blading () is fixed, the outer movable blading () comprising at least one fixing rod () extending through an orifice () of the outer drum (), the outer movable blading () being fixed to the outer drum () via a clamping means () fixed to the fixing rod () from an outer face of the outer drum (), a set ring () being disposed around the fixing rod () in the orifice () of the outer drum ().

Device for attaching blades in a contra-rotating turbine

A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.

Rotor for a contrarotating turbine of a turbine engine

The invention relates to a turbomachine assembly comprising: &#x2014;a casing comprising: &#x2014;an internal hub (), &#x2014;an external ferrule () extending around and at a distance from the internal hub (), &#x2014;a hollow arm (), provided with a longitudinal cavity () and connecting the internal hub () and the external ferrule (), &#x2014;a tube () configured to extend in the interior of the longitudinal cavity () of the hollow arm () of the casing and comprising a central support () comprising two elastic blades () and configured to exert a pressure on the wall () of the longitudinal cavity () when the tube () is extended in the interior of the longitudinal cavity (); characterized in that the material(s) of the elastic blades () is (are) such that said elastic blades () have a stress curve between the minimum and maximum stress curves of table A.

Central support for auxiliary tubes with elastic return

A support system () for a structural casing of a turbomachine (), which comprises:

Handling fitting with movable jaws for a turbomachine casing

A turbomachine element includes a stator, a rotor, and a first sealing means for sealing between the rotor and the stator. The element is arranged to be active when the rotor is in the operating position of same around the axis of rotation thereof. The element includes an auxiliary pressure sealing means, sealing between the rotor and the stator and is arranged so that the two sealing means are active when the rotor is placed along the axis of rotation thereof during an assembly operation in a test position. In the test position, the rotor and the stator form an enclosure between said two sealing means.

Turbomachine element comprising an auxiliary sealing means, and method for testing this element

An extraction sleeve for extracting two rotationally symmetrical parts that are joined together by interference fit, the extraction sleeve including: a head having a conical part; a cylindrical body, the internal part of the cylindrical body having a screw thread suitable for the screwing of an extraction screw; the conical part of the head of the extraction sleeve forming a friction component suitable for coming into contact with one of the rotationally symmetrical parts, the friction component being designed so as to determine a limit slipping torque greater than the friction torque generated at the screw thread of the sleeve by screwing of the extraction screw.

Extraction sleeve

A turbomachine including an exhaust housing, including a plurality of arms, the space separating the arms defining openings in which there circulates a primary air flow of the turbomachine, at least one conduit, a) configured to collect a compressed air flow at one of the ends of same, b) the other end of the conduit being connected to at least one opening of the exhaust housing, so as to insert the collected air flow into the primary air flow, the collected air flow having, when inserted into the opening, a Mach number less than or equal to 0.5.

Turbomachine with collection of a compressed air flow

A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins extending outwards in a radial plane from the annular portion, each fin forming an angle relative to the radial direction. The fins have fastener zones at their outer peripheries, the fastener zones being inclined in the axial direction of the support so as to be suitable for fastening to an exhaust cone of the turbine engine.

Air exhaust tube holder in a turbomachine

An exhaust housing hub of a turbomachine, including a connecting wall and an inner channel wall, the connecting wall connecting the inner channel wall to inner attachment flanges, wherein a radial section of the connecting wall is curved and can be formed, as required, as a single component with the inner channel wall, the hub also including a series of ribs extending radially between the connecting wall and the inner channel wall.

Exhaust housing hub for a turbomachine

Growing community of inventors

Moissy-Cramayel, France

Olivier Renon