Safran Aircraft Engines

Baghdad Achbari

Bruno Alexandre Didier Jacon

Hervé Simonotti

Thomas Claude Broage

Morgan Balland

Florent Robert André Godin

Faouzi Aliouat

Jean-Yves Picart

Soufien Akachkachy

Alban Francois Louis

Charles Maurice Jean-Louis Cheret

Joseph Taglialavore

Joël François Roudil

An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

Inlet cone for an aircraft turbomachine

A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.

Fire resistance device designed to be placed between one end of a mounting strut for an aircraft turbomachine and a cowling of said turbomachine delimiting an inter-flow compartment

An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

Air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element, and a nacelle element

An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member () attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

Outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, comprising improved air-sealing and fire-resistance devices

A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.

Fire resistance device intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment

Growing community of inventors

Moissy-Cramayel, France

Baghdad Achbari