Safran Nacelles

Aircelle Limited

Vincent Peyron

Jean-Nicolas Bouchout

Laurent Georges Valleroy

Hazem Kioua

Serge Bunel

Patrick Gonidec

Pierre Caruel

Patrick Boileau

Jean-Philippe Joret

Pascal Soulier

Arnaud Bonny

Flavie Hubert-Choinard

Emmanuel Lesteven

Alexandra Dugardin

Franck Depoortere

Jerome Lescure

Céline Blin

Guillaume Strub

Jérôme Lescure

Nicolas Bouchout

A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.

Thrust reverser provided with cable kinematics for scoop flaps

A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

Method for manufacturing a structural surface heat exchanger for a nacelle

An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

Aircraft nacelle comprising at least one heat exchanger

A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.

Surface heat-exchanger for a cooling system of an aircraft turbojet engine

A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.

Turbine engine nacelle comprising a cooling device

In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between &#x2212;70&#xb0; C. and +175&#xb0; C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).

Heat-transfer fluid for a cooling system of an aircraft turbojet engine

An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.

Thrust reverser with movable cascades for an aircraft propulsion unit and related mounting and dismounting methods

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

A propulsion unit for an aircraft is provided. The propulsion unit includes a stationary unit having at least one cowl pivotally mounted on an axis collinear with a longitudinal axis of the propulsion unit between an operating position or a maintenance position allowing access to the turbojet engine for regular maintenance operations and irregular maintenance operations. The maintenance position for irregular maintenance operations includes an opening angle of the cowl that is greater than the opening angle of the cowl to carry out regular maintenance operations. The propulsion unit further includes at least one cylinder and at least one safety connecting rod secured to the cowl and stationary unit.

Propulsion unit for an aircraft and method for opening a movable cowl of said propulsion unit

The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.

Cascade thrust reverser for an aircraft turbojet engine

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

A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod.

Turbojet engine nacelle with downstream section

A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device.

Thrust reverser device

An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.

Growing community of inventors

Le Havre, France

Vincent Peyron