Safran Aircraft Engines

François Marie Paul Marlin

Christophe Paul Jacquemard

Thierry Georges Paul Papin

Jacky Novi Mardjono

Christophe Marcel Lucien Perdrigeon

Cédric Zaccardi

Didier Gabriel Bertrand Desombre

Didier Queant

Mathieu Gaillot

Damien Daniel Sylvain Lourit

Laurent Paul François Perrot

Kévin Michel Robert Contal

Sébastien Nicolas Juigne

Stève Marcel Nicaise

Frédéric Imbourg

An aircraft propulsion assembly including a fan shaft which is connected to a turbine shaft by means of a reduction gear. The guiding of the fan shaft is carried out by a first bearing including cylindrical rollers and a second beating including two rows of balls with oblique contact.

Turbomachine fan assembly comprising a roller bearing and a double-row ball bearing with oblique contact

The invention relates to an assembly for holding an epicyclic gear train in a turbomachine comprising an annular housing in which are engaged a first annular part and a second annular part which are locked against rotation in the housing by first annular interlocking means and second annular interlocking means, respectively, wherein the first annular interlocking means are configured to allow a first circumferential clearance between the first annular part and the housing, the second annular interlocking means are configured to allow a second circumferential clearance between the second annular part and the housing, and the first circumferential clearance is strictly less than the second circumferential clearance.

Assembly for retaining a gear train in a turbomachine

A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume. The device includes an annular deflector positioned inside the annular volume so as to subdivide the annular volume into a first annular cavity and a second annular cavity, the second annular cavity being defined between the annular deflector and the outer annular wall of the splitter nose.

Device for de-icing a splitter nose of an aviation turbine engine

Growing community of inventors

Villiers sous Rez, France

François Marie Paul Marlin