Snecma

Damien Lourit

Fabrice Cretin

Regis Eugene Henri Servant

Thierry Georges Paul Papin

Alain Marc Lucien Bromann

Francois Marie Paul Marlin

Serge Louis Antunes

Yvan Guezel

Julie Bellay

A device for centring and guiding the rotation of a turbine engine shaft, in which the outer race of a bearing is retained axially upstream and downstream by a retaining mechanism cooperating with a bearing bracket and with a coupling mechanism including elastically deformable mechanism connecting the outer race to the bearing bracket, the retaining mechanism being separate from a protecting ring of the device. A method of assembling such a device is also described. The retaining mechanism is pre-assembled with the coupling mechanism prior to the final assembly of the coupling mechanism with the bearing bracket. The device and the method have the combined advantages of axially retaining the outer race in two opposing directions and having a particularly straightforward assembly.

Device for centring and guiding the rotation of a turbine engine shaft including improved means for retaining the external bearing ring

This invention relates to an assembly () for an aircraft turbofan comprising a flowpath splitter () downstream from which there is firstly a fan flowpath () inner delimitation ring () and secondly a compressor case (), the assembly comprising a plurality of outlet guide vanes () provided with an inner platform () located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part () to support the delimitation ring (), comprising a radially outer end () fixed to a downstream part of this ring () and a radially inner end () fixed to the compressor case ().

Aircraft turbofan comprising an intermediate ring with simplified downstream support

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Lieusaint, France

Damien Lourit