Safran Aircraft Engines

Bruno Alexandre Didier Jacon

Hervé Simonotti

Baghdad Achbari

Florian Benjamin Kévin Lacroix

Julien Vitra

Gonzague Marie Come Jacques André Elluin

Florent Robert André Godin

Thomas Claude Broage

Philippe Didier Edmon André Libéral Nabias

Damien Clément Didier Cordier

Antonin Etienne Diego Tessiereau

Faouzi Aliouat

Philippe Didier Edmond Andre Liberal Nabias

Damien Didier Clément Cordier

Cédric Antonio Da Silva

Soufien Akachkachy

Charles Maurice Jean-Louis Cheret

Joseph Taglialavore

Joël François Roudil

A sealing device composed of a lip seal and a spring or another resilient seal which radially and axially compresses the first seal, forming two sealing lines closed over substantially planar surfaces which are opposed in the direction of the protected rolling bearing axis. The device is small and lightweight and withstands the centrifugal forces in the lateral direction of the rolling bearing. It is possible to dispense with any further parts for retaining it. The space requirement is reduced, and assembly is easy. The sealing device is suitable for arrangements of variable-pitch propeller blade roots.

Sealing arrangement for a rolling bearing subjected to centrifugal forces

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 airtight seal configured to be mounted on a first turbomachine member, such as a door of a bleed valve, and to bear against a second member of the turbomachine, such as a hub of an intermediate casing, the airtight seal including a retaining device for mounting the seal on the first member; a sealing lip ensuring airtightness through contact and intended to bear against the second member; an anti-return device for the sealing lip reinforcing the rigidity of the airtight seal at the base of the sealing lip.

Airtight seal for bleed valve door of a turbomachine

A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

Seal for an intermediate turbomachine casing

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

An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L); and a second annular air-sealing lip extending from the attachment base over a second length (L) lower than the first length and facing the first lip.

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Moissy-Cramayel, France

Bruno Alexandre Didier Jacon