Airbus Operations Gmbh

Airbus Deutschland Gmbh

Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Sl

Holger Bammann

Frank Klimpel

Alexander Solntsev

Thomas Scherer

Dariusz Krakowski

Jens Schult

Bruno Stefes

Didier Poirier

Torsten Trümper

Hans Brunswig

Alexandre Broquet

Johannes Eichholz

Martin Sieme

Tim Giese

James Brown

Anton Mendez-Diaz

Thomas Selchert

Hugo Alexandre Duart Mendes Raposeiro

Heiko Rothe

Thomas Josset

Florent Huet

Paul Chen

Marion Gourgues

Hugo Alexandre Duarte Mendes Raposeiro

An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Auxiliary power unit for an aircraft

An aircraft air conditioning system comprising an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Aircraft air conditioning system and method of operating an aircraft air conditioning system

An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Aircraft air conditioning system with a cabin exhaust air turbine

An aircraft air conditioning system including an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

A ram air channel arrangement for ambient air supply into an aircraft comprises a ram air channel which has a ram air inlet channel and a ram air outlet channel arranged downstream of the ram air inlet channel and in fluid communication with the ram air inlet channel. The ram air channel arrangement further comprises a cabin exhaust air line which is adapted to have cabin exhaust air flow therethrough which has been removed from an aircraft cabin and which cabin exhaust air line is connected to the ram air inlet channel and is adapted to lead the cabin exhaust air into the ram air inlet channel.

Ram air channel arrangement and method for operating a ram air channel arrangement

An aircraft air conditioning system comprising an ambient air supply line with a first end connected to an ambient air inlet and a second end connected to a mixing chamber. A first electrically driven ambient air compressor in the ambient air supply line compresses the ambient air flowing therethrough. A first ambient air branch line branches off from the ambient air supply line upstream of the first ambient air compressor and rejoins the supply line downstream of the air compressor. A second ambient air compressor in the first ambient air branch line compresses the ambient air flowing therethrough. A cabin exhaust air line has a first end connected to an air conditioned aircraft area. A cabin exhaust air turbine in the exhaust air line is driven by the exhaust air flowing through the cabin exhaust air line and is coupled to drive the second ambient air compressor.

Aircraft air conditioning system with an electrically driven ambient air compressor and method for operating such an aircraft air conditioning system

An aircraft air conditioning system comprises a process air line configured to supply compressed process air provided by a process air source to an air conditioning unit of the aircraft air conditioning system and a trim air line branching off from the process air line upstream of the air conditioning unit and being configured such that trim air flows through the trim air line, the trim air having been branched off from the compressed process air flowing through the process air line. A compressor is arranged in the trim air line and is configured to compress the trim air flowing through the trim air line. A turbine of the aircraft air conditioning system is configured to drive the compressor. A cabin exhaust air line is configured to supply cabin exhaust air discharged from an aircraft cabin to the turbine for driving the turbine.

An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.

Gas exhaust diverter

A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air () within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.

Cooling air supply for the cooling of different systems requiring cooling air in an aircraft

Aircraft air-conditioning system () for an aircraft having a plurality of zones (), comprising a first line () for feeding cold air at an actual temperature T, a second line () which branches off a portion of the air from the first line () at a branching point () and feeds the air to a plurality of zones () of an aircraft, wherein warm air is fed through a first trim valve () into the second line () so that the air in the second line () is heated to the actual temperature T, and a first zone feed line () feeding the air downstream of the first trim valve () to a first zone (), wherein a second trim valve () is arranged in the first zone feed line (), through which valve warm air is fed into the first zone feed line () so that the air in the first zone feed line () is heated to the actual temperature Tzf, and the first line () downstream and/or upstream of the branching point () feeds cold air at least to one further zone. A second feed line () feeds air downstream of the first adjustment () to a second zone (). A heating device () can be arranged in the second feed line ().

Air-conditioning system with icing protection for an aircraft

A system () for cooling a thermally loaded device on board an aircraft comprises a distribution line () which is in communication with an installation space () of the thermally loaded device, a coolant supply line () which is in communication with a coolant source, and a heat removal line () which is in communication with a source of pressure below atmospheric pressure. A shut-off control device () is adapted so as, in a first position, to separate the distribution line () from the coolant supply line () and connect the distribution line () to the heat removal line () and, in a second position, to connect the distribution line () to the coolant supply line () and separate the distribution line () from the heat removal line ().

Growing community of inventors

Hamburg, Germany

Holger Bammann