Safran Aircraft Engines

Antonin Etienne Diego Tessiereau

Pascal Xavier Delaitre

Wouter Balk

Jean-Marc Claude Perrollaz

Romain Nicolas Lagarde

Thierry Kohn

Bruno Alexandre Didier Jacon

Bruna Manuela Ramos

Florian Benjamin Kévin Lacroix

Cyrille François Antoine Mathias

Florent Robert André Godin

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

The invention relates to an assembly for a turbomachine with a longitudinal axis comprising a first annular wall (), panels () being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall () so as to form a flow surface for a flow of air, each panel () being secured to the first annular wall () by at least one fixing member () passing through an orifice in the panel () and secured to the first annular wall () by means of a sleeve and a stud forming a spacer.

Bypass turbomachine

A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

Turbomachine including a cooling and turbine clearance control system having an air supply scoop

An air bleed device for an aircraft engine, including a frame and a flap able to rotate about an axis in relation to the frame, the device further including a return system configured to bias the flap in a determined position about the axis and including a torsion spring, a first end of which is connected to the flap and a second end of which is connected to the frame. The second end is connected to the frame by adjusting the preload of the spring by screwing when the flap is in the determined position.

Spring preload adjustment device for an aircraft engine air bleed flap

Growing community of inventors

Moissy-Cramayel, France

Antonin Etienne Diego Tessiereau