Snecma

Yoann Marechal

Pierre-Alain Jean-Marie Philippe Hugues Chouard

Emily Barnes

A turbojet engine with a fan and a nacelle element forming the secondary duct downstream of the fan is provided. The turbojet engine includes an intermediate casing with an outer shroud to which the nacelle element is fixed by a connecting member. The connecting member includes a cylindrical element secured to the shroud while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to the nacelle element by a bayonet-type fitting.

Turbojet engine with an element of the nacelle attached to the intermediate casing

A suspension rudder bar has the shape of a bar with a transversal axis (Y'Y), symmetrical with respect to a plane (P) intersecting the rotation axis (X&#x2032;X) of the engine, and includes links with transmission connecting rods between a rear casing for ejecting gases and a front casing hub of the fan, and a central link to a fastening fixation to an engine fastening pylon. The links of the rudder bar to the transmission connecting rods are arranged on the transversal ends of the rudder bar, and the rudder bar extends, perpendicularly to the axis of the bar (Y&#x2032;Y), with spars over a sufficient portion and at a determined distance from the edges of the plate to act as an abutment to the plate in the case of a torsion around the central link or of a connecting rod breaking.

Growing community of inventors

Dammarie-les-Lys, France

Yoann Marechal