Aircelle Limited

Safran Nacelles

Safran Aircraft Engines

General Electric Company

Snecma

Pierre Caruel

Patrick Boileau

Guy Bernard Vauchel

Patrick Gonidec

Jean-Philippe Joret

Olivier Kerbler

Peter Segat

Hervé Hurlin

Loïc Chapelain

Guillaume Glemarec

Gina Ferrier

Alexis Heau

Andre Baillard

Fabien Bravin

Fabien Charliac

Philippe Vancon

Alexandre Descamps

Bertrand Desjoyeaux

Bruno Albert Beutin

Laurent Georges Valleroy

Marc Versaevel

Vincent Peyron

Antoine Elie Hellegouarch

Pierre Moradell-Casellas

Nicolas Dezeustre

Denis Guillois

Hazem Kioua

Xavier Cazuc

Herve Hurlin

Carmen Gina Ancuta

Loïc Grall

Xavier Bouteiller

Sarah Tissot

Georges Alain Bouret

Mélody Seriset

Quentin Garnaud

Thierry Marin Martinod

Charles-Antoine Lampaert

Nicolas Maurice Herve Aussedat

Jean-Baptiste Manuel Nicolas Vignes

Sébastien Michel Thierry Guillemant

Franck Zaganelli

Mathieu Lerouvreur

Bertrand Leroyer

Shwetanjana Anand

Régis Giard

Mathieu Marc Christian Gaillot

Alexandre Francois Paul Louis Descamps

Peter Sagat

Regis Giard

André Baillard

Thiery Le Docte

An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.

Air intake module for an aircraft turbomachine and method for de-icing thereof

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

Suspension of a triple-flow aircraft turbine engine

An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

Aircraft propulsion unit

A thrust reverser for an aircraft propulsion assembly, this reverser including an outer structure movable between a closed position and an open position of two primary latches configured to lock the movable outer structure in the closed position. The movable outer structure includes an output end that is oblique with respect to the longitudinal central axis so as to orient the thrust laterally. In order to compensate the tilting moment of the movable outer structure, which results from this lateral orientation of the thrust, the primary latches are offset with respect to a median longitudinal plane passing through the longitudinal central axis of the reverser.

Thrust reverser comprising primary latches offset with respect to a plane of symmetry of the movable hood

A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.

Comprising an access space closed by a tangentially clamped cowl

An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

Acoustic attenuation panel and its manufacturing methods

A system for cooling a compartment for equipment in a nacelle having a member for drawing a cooling flow and a device for admitting the cooling flow into the compartment, having: a regulating member movably mounted with the ability to move in a first direction of movement limiting the admission when the internal pressure of the compartment is below the external pressure, and in a second direction of movement increasing the admission when the internal pressure is above the external pressure; a return member configured to keep the regulating member in a neutral open position and to damp the movement of the regulating member during modifications in the ratio of the pressures; a pressing member activated by a heat-sensitive element and configured to move the regulating number into a closed position so as to isolate the compartment in the event of fire.

Cooling system of a compartment of pieces of equipment in a nacelle of an aircraft propelling assembly

This summary relates to a thrust reverser for a turbojet engine mounted on an engine nacelle pylon, comprising a fixed part, a movable part, coaxial and mounted in translation with respect to the fixed part and sealingly inserted against the fixed part by blocking an air outlet passage in a closed state whereas the air outlet passage is freed up in the extended state, and a single actuating device including a beam, a slider, and a driving device, configured to drive the movable part in translation with respect to the fixed part, wherein the beam comprises a stop taking the form of a protuberance protruding on a radially outer surface of the beam and configured to have a clearance with respect to said engine nacelle pylon.

Thrust reverser for turbojet engine

The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position in which the shroud is attached to the stationary structure, and a spaced position in which the shroud is spaced from the stationary structure; at least one latch capable of holding the stationary structure and the shroud in the attached position; at least one actuator mounted between the stationary structure and the shroud and configured to move the shroud along the main axis between the attached position and the spaced position; and a seal configured to provide a seal between the stationary structure and the shroud in the attached position, wherein the seal has a tapered cross section.

Thrust reverser assembly for a turbojet engine

Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.

Air inlet of a turbomachine nacelle including a circulation conduit of a hot air flow between a movable upstream part and a fixed downstream part

A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

Thrust reverser comprising a single actuator for controlling a mobile cowling

A control system includes an actuator, a locking/unlock device, a central control valve, first and second control valves, and a spool control valve. The actuator is arranged so as to move a door of a thrust reverser between direct jet and reverse jet positions. The locking/unlocking device unlockable under load allowing locking and/or unlocking of the door. The locking/unlocking device is movable between a closure position in which it holds the door in the direct jet position and an opening position in which the door is released. The first and second control valves each fed by the central control valve. The spool control valve fed at least by the first and second control valves. The spool control valve is configured so that a pressure difference between two inlets of the first and second control valves provides a displacement of the spool control valve between first and second stable positions.

System for controlling a thrust reverser for a nacelle

An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.

Nacelle air intake and nacelle comprising such an air intake

A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.

Door-closing system for a thrust reverser of an aircraft nacelle

A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.

Rear assembly of an aircraft turbojet engine nacelle comprising a thrust reverser with sliding cascades

Growing community of inventors

Le Havre, France

Pierre Caruel