Safran Aircraft Engines

Hervé Simonotti

Bruno Alexandre Didier Jacon

Julien Vitra

Baghdad Achbari

Thomas Claude Broage

Florent Robert André Godin

Faouzi Aliouat

Soufien Akachkachy

Charles Maurice Jean-Louis Cheret

Joseph Taglialavore

Joël François Roudil

Bruno Jacon

A fire resistance device intended to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling equipping this turbomachine, the connecting cowling being intended 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 includes two contacting lips extending along different lines, of which a first lip with a C-shaped section is integrated within a contact structure, and a second lip including at its end a protruding blocking portion protecting the contact structure.

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

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

Hervé Simonotti