Aircelle Limited

Societe Hispano Suiza

Hispano Suiza Aerostructures

Societe Hispano Suiza Aerostructures

Societe Anonyme Dite Hispano-suiza

Hispano Suiza

Hurel Hispano

Aircella

Safran Nacelles

Herakles

Robert Standish

Jean-paul Rene Andre Hogie

Guy Bernard Vauchel

Patrick Gonidec

Pascal Gerard Rouyer

Pierre Andre Baudu

Jean-Philippe Joret

Stephane Beilliard

Pierre Caruel

Jerome Collier

Jean-Philippe Dauguet

Nicolas Hillereau

Georges Alain Bouret

Guillaume Lefort

Peter Segat

Andre Baillard

Vincent Joseph Studer

Jean Fabrice Portal

Guillaume Ruckert

Pierre Andre Marcel Baudu

Pierre-Alain Chouard

Laurent Georges Valleroy

Pierre Moradell-Casellas

Xavier Cazuc

Laurence Lemains

Pascal Lardy

Laurent Albert Blin

Christophe Thorel

Jean-Fabrice Marcel Portal

Eric Conete

Denis Guillois

Michel Philippe Dehu

Claude A Dubois

Eric Lecossais

Marc Gerome

Emmanuel Drevon

Jean-Marie L Gely

Philippe Avenel

Patrice Dhainault

Fabrice Henri Metezeau

Pascal-Marie P Soulier

Francois Conte

Jean-Marc D Marescot

Damien Beno&itilde;t Marie Lesbos

Regis Fassier

Pierre A Baudu

Jean-Paul Ren&eacute; Andr&eacute; Hogie

Pierre Andr&eacute; Marcel Baudu

Thierry Jacques Le Docte

Christophe Guenadou

André Baillard

Jean Philippe Joret

Peter Sagat

Jean-Francois Cribelier

Stéphane Beilliard

Fabien Bravin

Chiristophe Thorel

Jean-Philipe Joret

Stephanie Beilliard

Anne-Laure Gibouin

Serge Epherre-Iriart

Loïc Le Boulicaut

Renaud Barreteau

Frederic Zoonekyndt

Pierre André Marcel Baudu

Loïc Le Boulicuat

Pascal Gérard Rouyer

Jean-François Cribelier

Frédéric Zoonekyndt

Jérôme Collier

Jean-Philippe Dauget

François Conte

Jean-Philipp Joret

Jean-Paul Rene Andre Hogie

Pierre Baudu

Jean-Luc Mazzoni

A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.

Turbojet engine nacelle with variable ventilation outlet cross section

A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl.

Assembly including a reverse thrust device and system for actuating said device

The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles.

Self-mounted cascade for a thrust reverser

The invention relates to an assembly for a turbojet engine which includes a pylon () and a nacelle supported by said pylon (). Said nacelle () includes a grid thrust reverser () including an integral cowl mounted so as to slide on rails (), which are arranged on both sides of said pylon (), between a direct jet position and a thrust reversal position. Said assembly is characterized in that it includes means () for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon () and the cowl.

Assembly for an aircraft turbojet engine comprising a thrust reversal cowl

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

Turbojet engine nacelle () comprising an air intake structure () able to channel a flow of air towards a fan of the turbojet engine, and a central structure () intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel () incorporating an air intake lip () and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (), and a maintenance position in which the outer panel () is set away from the outer structure of the central section and the air intake lip () is set away from the inner panel of the air intake structure, characterized in that the longitudinal outer panel () is associated with guide means of the rails ()/slide () type, at least part of said guide means being positioned as close as possible to an interface with a pylon () to which the nacelle is attached.

Turbojet engine nacelle with translatable upstream cowl

The invention relates to a thrust reversing device () that includes at least one mobile cowling () mounted in translation in a direction substantially parallel to a longitudinal axis of a nacelle, capable of moving alternatively from a closing position on which it enables the aerodynamic continuity of the nacelle into an opening position in which it opens a passage in the nacelle for the bypassed flow, wherein said mobile cowling () also includes as an extension at least one variable nozzle section () including at least one panel () mounted so as to be capable of rotation, the panel () being adapted for pivoting towards at least one position entailing a variation in the nozzle section () on the one hand, and pivoting towards a position in which it blocks a cold flow jet () formed between a fixed structure of a turbojet fairing (and the nacelle on the other hand, wherein the mobile cowling () and the panel () are associated with actuation means () capable of activating the respective translation and rotation movements thereof, characterized in that said actuation means () are connected to an upstream end of the panel () by a driving connection rod () capable of moving about anchoring points respectively on the corresponding panel () and the associated actuation means ().

Thrust reversing device including variable nozzle section having first position for variation of the nozzle section and a second position for blocking a cold flow jet

An assembly to hold an interface of a stationary outer structure of a nacelle and a casing of a jet engine includes first and second raised elements and two half rings. The first raised element belongs to an upstream end of the stationary outer structure, and the second raised element belongs to a downstream end of the casing. The first and second raised elements are formed so as to be placed in contact with each other, and the two half-rings are formed by a wall and an abutment. The wall defines a housing to receive the first and second raised elements when the casing and the stationary outer structure are mounted edge to edge, and the abutment is formed so as to keep the first and second raised elements in the housing.

Assembly for holding the interface of stationary outer structure of a nacelle and housing of a jet engine

A thrust inverter for a turbojet engine nacelle includes an outer movable cowl and a front frame. The outer movable cowl translates between a closed position and a thrust inversion position and also moves to a supporting position in which the outer movable cowl is hinged and guided by a guiding member located on a pylon. In particular, the front frame holding cascade vanes is mounted downstream from an air blower housing, and part of the front frame is detachably connected to the air blower housing. The front frame is translatable along the guiding member once the front frame is detached from the air blower housing.

Thrust inverter with translatable cascade vanes having detachable front frame

The invention relates to a nacelle () for a turbojet engine () comprising: an air intake structure () able to channel a flow of air towards a fan () of the turbojet engine (), comprising an air intake lip () upstream of the nacelle () and attached at its ends to an outer panel () and an inner panel (); a central structure () intended to surround said fan () and to which the air intake structure () is attached in such a way as to ensure aerodynamic continuity, said central structure () comprising a secondary, or bypass, flow path outer ring section () intended to surround the engine and a central outer cowl (), and a downstream section (), the outer panel () comprising a moving part () attached to the air intake lip () and extending downstream of the inner panel () and at least one fixed part () fixed to the central structure () or to the downstream section () and intended to nest together with the moving part () through their having complementary shapes.

Turbojet engine nacelle

The invention relates to a securing plate () for removably securing a one-piece propulsion unit () to a wing of an aircraft, characterised in that it includes first connection means () for securing the plate to the wing, second connection means () for securing the one-piece propulsion unit to the plate and third connection means () for securing a pair of longitudinal handling members () to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.

Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit

The invention relates to a nacelle for an aircraft engine that comprises a front cowling () and a rear cowling (), the rear cowling () being mounted so as to slide between an upstream position defining a reduced nozzle () section and a downstream position defining an enlarged nozzle () section. The nacelle includes an intermediate member () arranged edge-to-edge with said front cowling (), said member defining a housing () for receiving the upstream edge () of said rear cowling () when the latter is in the upstream position.

Nacelle for aircraft engine having a nozzle with a variable section

The present invention relates to a thrust reversal device () for a turbojet engine nacelle, characterized in that: (i) the movable cowl () is provided with at least one driving lead screw () having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means () of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting () the rotational movement thereof towards at least one drive system () of the flap.

Thrust reversal device

A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm.

Airplane jet engine thrust reverser having gratings or cascades

The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing () intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (), characterized in that the casing extends around the fan more or less as far as the fan blades (), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange () capable of providing containment for at least one blade should the latter break off.

Nacelle for turbojet engine

Growing community of inventors

Harfleur, France

Guy Bernard Vauchel