Safran Aircraft Engines

Snecma

Giuliana Elisa Rossi

Eddy Stephane Fontanel

Eddy Stephane Joel Fontanel

Eddy Stéphane Joël Fontanel

Olivier Renon

Maxime Didier Delabriere

Philippe Pierre Vincent Bouiller

Florence Irène Noëlle Leutard

Gael Evain

Matthieu Fiack

Jean-Michel Boiteux

Christophe Lima

Julien Foll

Gaël Evain

Sebastien Bourget

Emmanuel Da Costa

Alberto Martin Matos

Abdelkader Benyahia

Marie Gentilhomme

Sébastien Bourget

Jérémy Lucien Jacques Bioud

Helene Orsi

Philippe Rembry

Florence Irene Leutard

Jeremy Lucien Bioud

Maxime Delabriere

Philippe Bouiller

Hélène Orsi

Maxime DELABRIÈRE

A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to the shaft. An air guide is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide passes between the first seal and the shaft, the air guide being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

Turbomachine bearing housing

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 journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the circumferential ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged radially between the airflows.

Journal for a turbine engine comprising a ring for recovering a flow of lubricating oil with a plurality of lubricating oil discharge ports

An apparatus for activating a valve of an ejector in order to adapt the pressurization of a chamber in an aircraft turbojet engine comprising a device constructed and arranged to trigger the opening and/or closing of valve and/or the power of the valve as a function of the altitude at which the valve is located.

Device for activating a passive ejector valve for pressurising a turbojet engine chamber for an aircraft

Growing community of inventors

Moissy-Cramayel, France

Giuliana Elisa Rossi