Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Maxime Zebian

Alain Porte

Arnaud Bourhis

Gregory Albet

Yannick Sommerer

Jacques Lalane

Florian Ravise

François Pons

Antoine Abele

Ali Kapekov

Thomas Livebardon

Davy Bourgalet

An aircraft having an engine, a cabin, an air conditioning system collecting the hot air from the engine, so as to treat the hot air, regulate a temperature of the hot air and send the hot air towards the cabin via a main line, an air line channeling the air leaving the cabin, and an arrangement for cooling the engine using the air thus drawn off by the air line. By drawing off the air at the outlet of the cabin, the performance of the engine is improved and the fuel consumption is reduced.

Aircraft having an engine and a system for cooling the engine

A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.

Module ensuring an attenuation of sound waves and a heat exchange

A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.

Aircraft propulsion assembly having a ventilation system and a fire-fighting system

A propulsion assembly with a primary duct and a secondary duct, an outer fairing delimiting an outer compartment with an inlet opening, an inner fairing delimiting an inner compartment with an air exhaust aperture, a suction system having an inlet, an outlet and mobile elements that draw the air in via the inlet and deliver the air via the outlet, a drive that drives the mobile elements, a transfer pipe connected to the outlet, a distribution pipe disposed in the inner compartment, connected to the transfer pipe and having nozzles, a supply pipe that opens into the outer compartment and is connected to the inlet, and a regulator that regulates the flow rate of air in the suction system. The outside air is then driven by the suction system and passes through the two compartments in a forced manner.

Aircraft propulsion assembly having a ventilation system

An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.

Aircraft with a fuel cell and a structure having a tank containing a heat-transfer fluid ensuring the cooling of the fuel cell

An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the inner shroud.

Aircraft engine nacelle comprising a system of ice protection

An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

Aircraft engine nacelle comprising an anti-icing protection system

A regulation system to regulate the flow rate of a hot air duct which comprises a shutter, an upstream air intake, a downstream air intake, a regulator and an actuator of the shutter with a first inlet connected to an outlet of the regulator and a cooling system comprising an outer radiator, a housing and a heat pipe housed in the housing and discharging the heat between the housing and the outer radiator, wherein the air streams coming from the upstream air intake and from the downstream air intake pass through the housing. Such a regulation system allows a better discharging of the heat by the action of the heat pipes.

Regulation system comprising a valve, a regulator, an actuator and a cooling system using heat pipes

A turbomachine for an aircraft, comprising a thermoacoustic system associated with a fluid circuit that serves to supply the engine of the turbomachine with fluid. The thermoacoustic system comprises an exchanger which is connected to the fluid circuit and in which there flows a fluid that is to be cooled, an acoustic attenuation structure which is distinct from the exchanger and which forms all or part of a wall of the fan duct, and at least one heat-duct tube comprising a portion that is entirely received in the acoustic structure and a portion with an end that is received in the exchanger, and a single curved elbow with a non-zero angle between the two portions.

Aircraft turbomachine equipped with a thermoacoustic system

A turbomachine for an aircraft comprising a thermo-acoustic system associated with a fluid circuit allowing the turbomachine engine to be supplied with fluid, the thermo-acoustic system comprising an exchanger connected to the fluid circuit and through which the fluid that is to be cooled passes, an acoustic noise-attenuation structure forming, in full or in part, a wall of the duct of a fan duct, the structure being situated some distance from the exchanger, and a pulsating heat pipe comprising a tube extending between the exchanger and the acoustic noise-attenuation structure, the tube having a serpentine form with a plurality of elbows bent over at 180&#xb0; housed alternately in the exchanger and the structure.

Turbomachine fitted with a thermo-acoustic system

A turbomachine comprising an engine body and an annular nacelle. The nacelle has an air intake comprising an outer skin, an inner skin, an air intake lip connecting the outer and inner skins together, and an annular frame connecting the outer and inner skins together. The turbomachine comprises a system for de-icing the air intake having an air bleeding port for bleeding a flow of hot air from the engine body, and two interconnected heating systems. An inner skin heating system receives the hot air flow to heat, by means of a gas-liquid heat exchanger, a heat transfer liquid contained in a hydraulic circuit arranged in part in the heat exchanger and in the inner skin. An air intake lip heating system diffuses the flow of hot air, once it has passed through the inner skin heating system, through the annular frame to heat the air intake lip.

Turbomachine having an air intake de-icing system

A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.

Aircraft turbomachine comprising a compartment equipped with a ventilation assembly

A structure ensuring acoustic attenuation of a flow of a first fluid and heat exchange between a first fluid and a second fluid. The structure includes a first wall which is perforated, a second wall, and a plurality of intermediate walls extending between the first wall and the second wall. For each intermediate wall, there is a pipe intended to receive the second fluid and inscribed within the intermediate wall. Such a structure makes it possible to optimally integrate the acoustic wave attenuation function and the heat exchange function.

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Saint-Sauveur, France

Maxime Zebian