Safran Nacelles

Safran Ceramics

Thierry Jacques Albert Le Docte

Thierry Guy Xavier Tesson

Christophe Paul Aupetit

Philippe Avenel

Virginie Emmanuelle Anne-Marie Digeos

Christophe Jean François Thorel

Caroline Coat-lenzotti

An annular air intake lip for a nacelle of an aircraft propulsion assembly is provided. The annular lip can extend about an axis of revolution and include: an external annular wall, an internal annular wall, an upstream annular wall connecting the external and internal annular walls to define an annular cavity therebetween. At least part of the annular lip can include at least one heat transfer coating that is made from a carbon allotrope material.

Air intake lip for a nacelle of an aircraft propulsion assembly

The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone () comprising a radially outer annular wall () defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (), the sound box comprising a radially inner annular wall (), —a connecting member () intended to be axially inserted between the exhaust housing and the ejection cone (), the connecting member () comprising an upstream annular flange () intended to be attached to the exhaust housing and a plurality of downstream securing tabs () connected to the inner annular wall (), —an annular sealing shroud () comprising an upstream portion surrounding the securing tabs () of the connecting member () so as to cover the spaces circumferentially located between the securing tabs () and axially located between the upstream annular flange () of the connecting member () and the radially inner annular wall ().

Sealing assembly for a turbine ejection cone

The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.

De-icing device for an air intake of an aircraft turbojet engine nacelle

Growing community of inventors

Moissy-Cramayel, France

Thierry Jacques Albert Le Docte