Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Airbus Deutschland Gmbh

Airbus France

Guillaume Bulin

Patrick Oberle

Thierry Surply

Jean-Michel Rogero

Nicolas Devienne

Severine Perret

Christian Fabre

Ralf-Henning Stolte

Christophe Cros

Jan Dittmar

Paul-Emile Roux

Fabre Christian

Stephane Pugliese

Pierre Calvairac

Pierre Jacquet Francillon

Nicolas Lecointre

Stéphane Pugliese

Armand Ruggeri

Matthieu Ritter

Juluan Gaultier

Séverine Perret

The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

Aircraft comprising a control device for a jet pipe nozzle with variable cross-section powered by two independent electrical power supplies

A variable cross-section nozzle of an aircraft has at least two movable parts enabling modification of the cross-section of the nozzle. A control device for the nozzle includes a system for regulating the engine, the system being connected to a control element which drives at least one electric motor which creates the movement of the movable parts, including an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor.

Device for controlling a nozzle of variable cross-section of an aircraft

An aircraft propulsion unit comprising a nacelle with a fan cowl locking and closing mechanism. The fan cowls of the nacelle can be closed by a single operator in accordance with the ergonomic standards defined for a single individual. A nacelle is provided with a lateral locking mechanism configured to keep one of the two fan cowls in the closed position, so as to reduce the spacing between the two lower sides of the fan cowls, whereas the presence of a stop between a first elastic member provided on one fan cowl and a second elastic member provided on the other fan cowl allows the operator to provide only that effort required to overcome the force exerted by a single spring at a time.

Aircraft propulsion unit comprising a nacelle provided with a fan cowl locking and closing mechanism

A control device for controlling a variable section nozzle of an aircraft power plant, the variable section nozzle including one or several movable parts capable of modifying the nozzle section and connected by a mechanical transmission chain to an actuator. The control device includes a system for regulating the power plant connected to a control member configured to control the actuator. The control device includes a single control member, an immobilization unit configured to immobilize all the movable parts which are deactivated only when the regulation system controls the positional change of the movable part or parts and a determination unit configured to determine the actual position of the movable part or parts.

Device for controlling a variable section nozzle of an aircraft

A fluid cooling device for the propulsion unit of a propfan type aircraft including a compressed air intake at the air compressor of the turbomachine, an air vein capable of conveying the collected compressed air to a cooler, and a system for conveying the heat of the lubricant to the cooler is provided. The cooler includes a matrix body provided with a plurality of ducts for a cooling agent, the ducts extending along a first inner surface up to a second outer surface of the matrix body such that the collected pressurized air serving as a cooling agent can pass through the matrix body, the matrix body of the cooler forming a portion of the outer skin of the propulsion unit; and a set of fins extending from the outer surface towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction when the aircraft is in flight.

Fluid-cooling device for a turbine engine propulsive unit

A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades.

Deicing device for propfan-type propeller blades

An air discharging device () for an aircraft turbine engine, comprising at least one door () displaceable between an open and a closed position of a corresponding orifice () and comprising two valves (), which delimit between them a conduit () for guiding a portion () of the secondary flow () outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (), so that in said open position, the upstream end of said internal valve () protrudes from the inner side relative to the internal surface (), the downstream end of said external valve () protrudes from the external side relative to the external surface (), and said internal valve () is spaced away from the fixed structure () so that an air passage exists downstream of said internal valve (), between the latter and said fixed structure ().

Air discharging device for an aircraft double-flow turbine engine

An electrical energy generating device for a propfan-type aircraft propulsion unit rotor. The propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit. The turbomachine generates a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown, and includes, within the moving annular part, a mechanism to transform thermal energy into electrical energy, preferably by thermal diodes. Such a device, as an example, can find application to a device for controlling a pitch of rotors of a propfan-type propulsion unit.

Electric generator disposed on a rotating turboprop part

A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of the outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown. The deicing device includes: a mechanism transforming thermal energy into electrical energy, within the moving annular part; a mechanism transferring the generated electrical energy towards the rotor blades; and a mechanism transforming the electrical energy into thermal energy onto at least a part of the surface of the blades.

Electric deicing device for propfan-type propeller blades

The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

Turboreactor for aircraft

Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine.

Ancillary device with an air turbine for taxiing an aircraft on the ground

A process for management of thermal effluents of an aircraft that includes an airframe () and at least one propulsion system (), whereby the at least one propulsion system () includes a gas turbine engine () that is supplied with fuel via a fuel supply circuit () that extends from a reservoir () that is arranged at the airframe (), whereby the airframe () includes at least one source of thermal effluents (), wherein the process includes at least partially dissipating&#x2014;at the level of at least one propulsion system ()&#x2014;the thermal effluents that are generated at the airframe () by using as coolant the fuel that is used for supplying the gas turbine engine ().

Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method

A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Nacelle with a displacement device for aircraft jet engine and aircraft including such nacelle

A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulating in the cell cooling circuit and air flow channeled into a cooling air channel extending from an air intake to an exhaust; and a second heat exchanger ensuring a heat transfer between the coolant circulating in the cell cooling circuit and the fuel. The air intake includes a blocker to open/close it. The system includes a fuel transfer circuit, which connects the fuel tank to the second heat exchanger and provides fuel to the second heat exchanger, including a valve selectively changing a fuel supply direction from the second heat exchanger between the directions of the tank and the fuel supply circuit.

System for managing the heat fluxes of an aircraft

A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.

Growing community of inventors

Blagnac, France

Guillaume Bulin