Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Airbus Deutschland Gmbh

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Ralf-Henning Stolte

Uwe Wollrab

Christian Mueller

Johannes Lauckner

Torben Baumgardt

Claus Hoffjann

Guillaume Bulin

Hansgeorg Schuldzig

Bruno Stefes

Volker Baumbach

Volker Piezunka

Carsten Weber

Paul Rohrbach

Harald Gründel

Sebastian Mock

Udo Krause

Hubert Gans

Gwenaelle Renouard-Vallet

Herman Jansen Van Vuuren

Remy Reynaud

Harald Gruendel

Rainer Beuermann

Gwenaelle Renouard Vallet

Michael Koenig

Florian Elken

Ralf Peck

Florian Eilken

André Brauer

Michael König

A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet.

Fuel cell system for an aircraft, method for operating a fuel cell system in an aircraft and aircraft with such a fuel cell system

An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.

Aircraft tail region with a cooling system installed in aircraft tail region

A fuel supply unit () for a fuel cell system which is in particular suitable for use in an aircraft comprises a fuel tank () and a feed line (), which connects the fuel tank () to an inlet () of a fuel cell (). A tank isolation valve () is disposed in the feed line (). A removal line () connects an outlet () of the fuel cell () to an unpressurised region of the aircraft and/or the outer atmosphere. The fuel supply unit () also comprises a sensor () for detecting an electrical voltage in the fuel cell () and an electronic control unit () which is adapted to receive signals output from the sensor () and which is adapted to detect a fault caused by an unintentional opening or a failure of the tank isolation valve () based on the sensor signals, when in a quiescent operational state of the fuel cell system electrical energy is generated by the fuel cell ().

Fuel supply unit for a fuel cell system, fuel cell system and method for monitoring a fuel supply unit

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 system for supplying an aircraft with inert gas is provided. The system includes at least one fuel cell with an air inlet and an exhaust air outlet as well as a membrane device with an inlet, an outlet and a vapor-permeable membrane. The exhaust air outlet is in fluid communication with the inlet of the membrane device. The membrane device guides a gas from the inlet to the outlet and to give off to the outside through the membrane any water vapor contained therein. This leads to a cost efficient, passive and reliable dehumidifaction of inert exhaust gas for inerting purposes, and a dehumidification device that does not or only marginally increases the weight of the aircraft.

System for supplying an aircraft with inert gas, method for supplying an aircraft with inert gas, use of a membrane and aircraft

In an embodiment, a fuel cell system for supplying emergency power to an aircraft, includes a fuel cell, a hydrogen tank, an oxygen tank, and a power distribution unit. This provides for an emergency power supply for aircraft that is reliable, independent of the outside air, and has low maintenance needs.

Fuel cell emergency system

A fuel cell system having an apparatus for gas drying that includes, but is not limited to at least one cooling element with at least one first surface and at least one detachment device. The cooling element is designed to be thermally connected to a heat sink and to come into contact with gas flowing past. The detachment device is movably held relative to the first surface and is designed to detach frozen water from the first surface.

Fuel cell system and method for drying of exhaust gas of a fuel cell system

An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means.

Emergency supply system for a transportation means, method for supplying electrical power and for inhibiting fire and aircraft with an emergency supply system

A system for reducing harmful substances in engine exhaust gases includes a fuel cell, which is adapted to generate electrical energy and a steam-containing fuel cell exhaust gas during operation. A fuel tank serves to store fuel which is to be supplied to an engine during operation. A condensing device is connected to an exhaust gas outlet of the fuel cell so that steam-containing fuel cell exhaust gas is supplyable to the condensing device. The condensing device is adapted to convert the steam contained in the fuel cell exhaust gas into the liquid state of aggregation by means of condensation and to introduce the water obtained as a result of the condensing process into the fuel in order to form a water/fuel mixture. A water/fuel mixture line is connected to the engine so that a water/fuel mixture is supplyable to the engine.

System and process for the reduction of harmful substances in engine exhaust gases

The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention is characterized in that the air delivery means is connected to an air-conditioning system of the aircraft for discharging air from the cabin of the aircraft via an air heating device, wherein the air heating device is connected to at least one heat source in order to heat the air from the cabin of the aircraft. The de-icing system according to the invention is able to realize a wing de-icing that not only fulfills an anti-icing function, but also a de-icing function on the ground without additional expenditure of energy. The function of the de-icing system according to the invention could also be advantageously supplemented by utilizing the cabin waste air for increasing the flow energy on the upper side of the wing in order to delay a change-over or separation of the boundary layer and to generally increase the lift or lower the resistance.

De-icing system for an aircraft

This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. The matrix body of the cooler is designed to form a section of the outer skin of the aircraft.

Cooler for an aircraft cooling system, aircraft cooling system and method for operating an aircraft cooling system

A safety system for reducing the explosion risk of a fuel tank comprises at least one fluid source and at least one fluid container with an inlet and an outlet for a fluid, wherein the fluid container has a structure that is flexible at least in some regions and is designed in such a manner that it can be positioned in a hollow space of the fuel tank, which hollow space is situated above the fuel, with said fluid container when fluid flows into the hollow space essentially occupying the space up to the top of the fuel tank. In this way it is possible to avoid the presence of a free air volume in the fuel tank, which counteracts any formation of a potentially explosive mixture and in this way reduces the explosion risk.

Safety system for reducing the explosion risk of a fuel tank

A power distribution system for an aircraft having at least one engine includes at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to an interior region of the aircraft fuselage, and at an end pointing away from the engine has at least one interface for introducing a torque. At the interface of the torque transmission means it is possible both to operate mechanical and to start the engine. Consequently in the aircraft it is possible to essentially do without converting mechanical energy to electrical energy and the subsequent use of electrical energy for generating mechanical power. This is particularly favorable in the case of twin-engine commercial aircraft that are used on short hauls.

Power distribution system

An aircraft cooling system () comprises a cooling element (), which comprises a housing (), a cooling air inlet () formed in the housing () and a plurality of heat exchangers (), which are disposed on lateral surfaces () of the housing () and through which cooling air supplied through the cooling air inlet () may flow. A cooling air supply channel () connects a cooling air supply opening (') formed in a tail section of an aircraft to the cooling air inlet () of the cooling element (). A cooling air outlet channel () connects the heat exchangers () of the cooling element () to a cooling air discharge opening ().

Aircraft cooling system

An energy supply system for an aircraft comprises at least one fuel cell and at least one energy storage device, wherein the fuel cell, of which there is at least one, is coupled to the energy storage device, of which there is at least one, such that the energy storage device can be charged by means of the fuel cell.

Growing community of inventors

Hamburg, Germany

Ralf-Henning Stolte