Safran Aircraft Engines

Snecma

Eddy Stéphane Joël Fontanel

Olivier Renon

Gerard Philippe Gauthier

Laurent Donatien Behaghel

Wilfried Lionel Schweblen

Florence Irène Noëlle Leutard

Mathieu Jean Pierre Trohel

Benjamin Philippe Pierre Pegouet

Matthieu Fiack

Jean-Michel Boiteux

Giuliana Elisa Rossi

Christophe Lima

Matthieu Etienne Attali

Julien Foll

Sébastien Gameiro

Emmanuel Da Costa

Abdelkader Benyahia

Alberto Martin Matos

Gaël Evain

Marie Gentilhomme

Jérémy Lucien Jacques Bioud

Gérard Phillippe Gauthier

Sébastien Bourget

Philippe Rembry

Gérard Philippe Gauthier

Hélène Orsi

Maxime DELABRIÈRE

Philippe Bouiller

An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

Emergency ventilation device for a turbine of a turbine engine, triggered by the melting of a locking means

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

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

Eddy Stéphane Joël Fontanel