Safran Aircraft Engines

Pascal Xavier Delaitre

Antonin Etienne Diego Tessiereau

Jean-Marc Claude Perrollaz

Romain Nicolas Lagarde

Thierry Kohn

Florian Benjamin Kévin Lacroix

Bruna Manuela Ramos

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

Evry, France

Pascal Xavier Delaitre