Snecma

Safran Aircraft Engines

Julien Foll

Olivier Belmonte

Philippe Pierre Vincent Bouiller

Eddy Stephane Joel Fontanel

Alexandre Tan-Kim

Giuliana Elisa Rossi

Benjamin Petard

Claude Dejaune

Stephane Bois

Emmanuel Da Costa

Arnaud Accary

Benjamin Kiener-Calvet

Stéphane Bois

Philippe Bouiller

A fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.

Fan disk for a jet engine and jet engine

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

A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds and being secured thereto. The part is made of composite material and is obtained by densifying a fiber preform with a matrix. The fiber preform includes a set of yarns extending continuously along a path passing longitudinally along the preform portions of at least two consecutive vanes by passing through the inner shroud preform portion and the outer shroud preform portion, and the woven fiber reinforcement yarns extends continuously in the circumferential direction along an inner shroud segment and along an outer shroud segment between which the consecutive vanes extend.

Turbine engine part forming a compressor stator or a turbine nozzle, and method for fabricating same

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Lucy, France

Julien Foll