Aircelle Limited

Safran Nacelles

Serge Bunel

Vincent Peyron

Jean-Philippe Joret

Hazem Kioua

Alexandre Bellanger

Jérôme Corfa

Xavier Bouteiller

Arnaud Bonny

Pascal Soulier

Jerome Lescure

Jérôme Lescure

The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.

Rear assembly of a turbojet engine nacelle including a fireproof sealing device

The present disclosure provides a device for locking a first cowling and a second cowling of a thrust reverser of an aircraft propulsion assembly. The cowlings are mounted such that each cowl pivots around a longitudinal axis between a closed flight position and an open maintenance position. The locking device includes a telescopic connecting rod having at least one sliding shaft, a locking mechanism on a proximal end of a shaft on the second cowling, and a connecting rod support. The connecting rod support or the tubular element includes two walls each delimiting a hole, and the tubular element of the connecting rod or the connecting rod support has two support fingers which each extend longitudinally on a side of the tubular element into a hole. The holes engage with the support fingers when the cowlings are open and allow free movement of the support fingers in a closed-cowlings configuration.

Locking device for pivoting cowls of a thrust reverser

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

A device for connecting a thrust reverser front frame to a fan casing includes a crenulated flange secured to the front frame, an annular component to accept this flange secured to the fan casing, and a crenulated annulus of a shape that complements the flange and pivot-mounted on the annular component. The crenulated flange, the annular component and the crenulated annulus are designed in such a way that a rotation of the annulus with respect to the annular component has the effect of locking this flange against this annular component through the collaboration between the respective crenulations of the flange and of the annulus.

Device for connecting a thrust reverser front frame to a fan casing and nacelle incorporating such a device

The invention relates to a seal () designed to be inserted between a nacelle element and an element of a turbojet of an aircraft propulsion unit. According to the invention, the seal () consists of at least two parallel tubular parts () each having a quadrangular cross-section including a planar supporting face (), a convex contact face () in contact with an element to be sealed and two concave side faces () connecting the convex contact face () and the planar supporting face (), said two tubular parts () being formed by a knitted web coated with a synthetic matrix.

Growing community of inventors

Le Havre, France

Serge Bunel