Safran Aircraft Engines

Damien Daniel Sylvain Lourit

Adrien Jacques Philippe Fabre

Pierre Jean-Baptiste Metge

François Marie Paul Marlin

David Khalil Charrier

A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.

Separation nozzle for aeronautic turbomachine

The invention relates to a bellcrank for a turbomachine having a first bore, a second bore and a third bore, the first bore being connected to the second bore by a first branch, the second bore being connected to the third bore by a second branch, the third bore being connected to the first bore by a third branch, a fourth branch connecting the first branch to the second branch.

Bellcrank for 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.

Growing community of inventors

Moissy-Cramayel, France

Damien Daniel Sylvain Lourit