Airbus (sas)

Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Airbus Operations Sl

Airbus Corporation

Jorge Alejandro Carretero Benignos

Lionel Czapla

Benedikt Bammer

Thomas Scherer

Alexander Solntsev

Jürgen Steinwandel

Benjamin Thubert

Christian Metzner

Michael Hofmann

Olivier Verseux

Alistair Forbes

Uwe Beier

Alexis Pissavin

Antoine Abele

Darren Paget

Nandakumar Devasigamani

Abhishek Verma

Kristian Zimmermann

Ludovic Ybanez

Lucien Prisse

Maria Del Sagrario Juanas Fernandez

Jorge Molano Rembiasz

Frank Hermle

An electric machine includes windings for creating electromagnetic fields and at least one fluid-tight internal housing. The group of windings is in an interior space of one of the at least one internal housing. Each of the at least one group of the windings includes at least two electric connecting sections for connecting the respective group of the windings to an external electrical circuit, wherein the at least two electric connecting sections reach from the interior space through a wall of the respective internal housing to outside the respective internal housing, wherein the at least one internal housing includes a coolant inlet and a coolant outlet, and wherein neighboring windings of the at least one group of the windings enclose gaps between each other, the gaps being in fluid communication with the respective coolant inlet and the coolant outlet to be flown through by a coolant.

Electric machine with directly cooled windings

A method for combined cooling and heating in an aircraft, the aircraft including an engine configured to use dihydrogen as fuel, the dihydrogen being stored in liquid form in a tank and being used in gas form in the engine, the dihydrogen being conveyed from the tank to the engine by a main pipe. The method includes the steps of branching off a part of the flow of dihydrogen in a bypass pipe, in parallel with a predefined segment of the main pipe, circulating a first heat transfer fluid in a first closed circuit, carrying out a first heat exchange between the first heat transfer fluid and the dihydrogen circulating in the bypass pipe and carrying out at least one secondary heat exchange. Each secondary heat exchange is carried out between the first heat transfer fluid and a working fluid used in the aircraft which needs to be cooled.

System for combined dihydrogen heating and fluid cooling for an aircraft, and aircraft comprising such a system

A component for an aircraft and an aircraft with such component. The component includes a heat source enclosed by a housing, heat exchanger, heat sink, at least one structural suspension element, and an air duct. Each structural suspension element is attached to an inner surface of the housing and supports one or more of the heat source within the housing. The heat sink is part of the housing and configured to guide air from an inside of the housing an outside of the housing. Each heat exchanger is thermally coupled to the heat source. Each heat exchanger is fluidly connected to the heat sink via an inlet line and a return line for a coolant. The air duct is configured to guide ambient air from the outside through the housing, past each of the at least one structural suspension element, and through the heat sink out of the housing.

Structural cooling system for an aircraft

A cooling device for use in alternating magnetic fields include an evaporator part defining a first volume for evaporating a cooling medium contained therein, the evaporator part being made of an electrically and magnetically non-conductive material, and a condenser part defining a second volume for condensing the cooling medium contained therein, the condenser part being in fluid connection with the first volume.

Cooling device for use in alternating magnetic fields, coil arrangement, electric machine, and aircraft

A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.

Heat exchanger limiting the risk of contamination between two fluids and aircraft comprising at least one such heat exchanger

An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Electric propulsion unit of an aircraft comprising a cooling system incorporating at least one front air inlet and aircraft comprising at least one such electric propulsion unit

A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

Propulsion assembly for an aircraft

An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

Aircraft comprising a hydrogen supply device incorporating a hydrogen heating system positioned in the fuselage of the aircraft

Growing community of inventors

Taufkirchen, Germany

Jorge Alejandro Carretero Benignos