Aircelle Limited

Safran Nacelles

Alexandre Bellanger

Florent Bouillon

Laurent Dubois

Patrick Gonidec

Serge Bunel

Stéphane Bardin

Emmanuel Anfray

The present disclosure relates to a thrust reverser device for a turbo jet engine nacelle including a fixed thrust reverser support structure having a longitudinal support half beam able to support a thrust reverser half-cowl, and the thrust reverser half-cowl mounted such that it can slide on the fixed structure in a direction substantially parallel to a longitudinal axis of the device via a guidance assembly, between a direct-jet position and a reverse-thrust position. In particular, the fixed structure includes a structure for offsetting the guidance assembly that guides the half-cowl circumferentially in a plane radial to the longitudinal axis between its various positions with respect to the half-beam on which the half-cowl is mounted.

Fixed structure of a thrust reverser device

An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section

The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Beam for a cascade thrust reverser

A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Nacelle for a bypass turbofan engine

A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam.

Nacelle for an aircraft engine

A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.

Growing community of inventors

Le Havre, France

Alexandre Bellanger