Aircelle Limited

Safran Nacelles

Xavier Bouteiller

Jean-Philippe Joret

Sarah Tissot

Patrick Gonidec

Pierre Caruel

Olivier Kerbler

Xavier Cazuc

Peter Segat

Jérôme Corfa

Serge Bunel

Laurent Albert Blin

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 concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.

Nacelle for an aircraft engine with variable section nozzle

The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.

Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors

A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

Flattened nacelle of a turbojet engine

A turbojet engine nacelle includes at least one nacelle element having a wall delimiting a main flow channel. The flow channel has a variable flow passage section. The cross-sectional area of at least one first area of the channel is greater than that of at least one second area of the channel. The turbojet engine nacelle further includes at least one secondary flow conduit establishing a fluidic connection between the first area and the second area of the channel and is arranged parallel to the channel. The wall of the nacelle element is at least partly covered by an acoustic damping panel extending in said areas of the channel. The conduit passes through the acoustic damping panel in order to establish the secondary flow via the acoustic damping panel. The present invention can be used in the avionics field.

Growing community of inventors

Deville les Rouen, France

Xavier Bouteiller