Aircelle Limited

Safran Nacelles

Peter Segat

Pierre Caruel

Guy Bernard Vauchel

Jean-Philippe Joret

Sarah Tissot

Georges Alain Bouret

Patrick Boileau

Xavier Bouteiller

Andre Baillard

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

A thrust reverser device for an aircraft turbojet engine includes: a movable cowl, translating cascades connected to the movable cowl, a mast; and a front suspension to suspend the turbojet engine. The cascades translates between a direct jet position where the cascades are retracted in a fan casing, and an indirect jet position where the cascades are brought out of the fan casing. In particular, the cascades have a sliding connection with the mast by means of at least one spacer connected to the mast downstream of the front suspension.

Thrust reverser device

A thrust reverser for a turbojet engine nacelle includes a movable cowl, cascade vanes and a portion forming a movable variable nozzle. The cowl translates between a closing position and a maintenance position which is located beyond a thrust reversal position. In the maintenance position, the cowl opens a passage within the nacelle and allows access the inside of the nacelle. The variable nozzle is translated by an actuator between reduced ejection section and increased section positions. In particular, the cascade vanes move between retracted and active positions and are housed in an envelope formed by a fan casing and an outer cowl in the retracted position. In the active position, the cascade vanes are displaced downstream by an actuator through a passage open by the movable cowl in the nacelle. The actuator of the cascade vanes is dissociable from the actuator driving the variable nozzle.

Thrust reverser with retractable cascade vanes

The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value.

Movable cascade turbojet thrust reverser having translatable reverser cowl causing variation in jet nozzle

The invention relates to a bent connecting rod () for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point () that are designed so as to enable the pivotal movement of the connecting rod () relative to said first and second assemblies, respectively, the bent connecting rod () being suitably positionable such that the bend () is located upstream from said flow relative to said second pivot point (), said second pivot point () being suitably built into the second movable assembly, characterized in that the bent connecting rod () includes at least two portions () linked together by at least one self-aligning means ().

Bent connecting rod fitted with at least one self-aligning means

An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring.

Arrangement of thrust reverser flap link rods on the internal fixed structure of a turbojet engine nacelle

A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.

Turbojet engine nacelle including a device for absorbing circumferential stresses

A nacelle includes a downstream structure having an outer structure, a concentric inner structure surrounding a downstream portion and an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, the inner and outer structures define an annular flow channel. The nacelle includes a guiding system for connecting the inner structure and downstream portion or a portion of a suspension mast, the system combines a translation and rotation movement of at least a portion of the inner structure between a working position, where the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position where the inner structure exposes the turbojet downstream portion and enable movement of the portion of the inner structure along the profile of the upstream section having a relatively small diameter, and the downstream section having a relatively large diameter.

Growing community of inventors

Le Havre, France

Peter Segat