Liebherr-aerospace Toulouse Sas

Liebherr-aerospace Lindenberg Gmbh

David Lavergne

Guillaume Galzin

Fabrice Laborde

Jean-Raymond Blary

Alfred Sauterleute

Frédéric Sanchez

Laurent Fayolle

Laurent Hartenstein

Cyril Vaucoret

Julien Daumas

Patrick Favreau

Karin Prince

Hubert Kresser

Markus Hirschmann

Vinciane Mille

Air conditioning system for a cabin () of an aircraft, comprising: an air bleed device; an air cycle turbine engine (); at least one main cooling exchanger (); a water extraction loop (); and a pipe () for distributing water extracted by said extraction loop (), characterized in that said system further comprises means () for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel () which supplies said main exchanger ().

Air conditioning system for an aircraft cabin, comprising means for reheating the water collected by the water extraction loop

System for protecting an outer surface of an aircraft comprising at least two fuel cells () from icing, characterized in that it comprises a first and a third liquid circuit () each causing a cooling liquid of the fuel cells () to flow, a second and a fourth liquid circuit () each causing an icing protection liquid to flow, at least two icing protection heat exchangers (--) arranged on the outer surface of the aircraft and having each icing protection liquid pass through them when it flows in the second or fourth liquid circuit (), and two liquid-liquid heat exchangers () in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.

System for providing protection from icing using a fuel cell

The invention relates to an electrical air conditioning system for air conditioning a cabin () of an aircraft comprising a source () of fresh air, a dynamic air circulation duct (), a motorized compressor () comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine () comprising at least a first compressor () and a first turbine () that are mechanically coupled to one another, said first compressor comprising an air inlet that can be connected either to said primary cooling exchanger (PHx) or to said source () of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine () comprising an air inlet that can be connected either to a discharge port () for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet that can be connected either to said cabin () or to an air injector () opening into said dynamic air duct.

Aircraft cabin electrical air conditioning system comprising a motorized compressor and an air cycle turbomachine

Exchanger () for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels () for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels () each extending adjacently to a secondary channel (); water-spray micro-perforated hollow bars () each extending adjacently to a primary channel () and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.

Exchanger for cooling warm primary air with cool secondary air and system for air conditioning provided with such an exchanger

The invention relates to a module () for recovery of energy of an aircraft cabin () comprising at least one air outlet () from the cabin and at least one fresh air inlet () into the cabin, the said module comprising: a turbine engine () comprising a compressor () and a turbine () mechanically coupled to one another; a cabin-air recovery duct () designed to be able to link the air outlet () from the cabin and the said turbine (); a cabin-air injection duct () designed to be able to link the compressor () and fresh air inlet () into the cabin; an emergency duct () designed to be able to link a high-pressure air source and the said turbine (); a control unit () configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine () is exclusively supplied by the air evacuated from the cabin (), or an emergency mode, in which the said turbine () is exclusively supplied by the air provided by the high-pressure air source.

Autonomous aircraft cabin energy recovery module and corresponding method

The invention relates to a system for environmental control of an aircraft cabin (), comprising a device for bleeding compressed air from at least one aircraft engine; an air cycle turbine engine () comprising at least one supercharger () connected to said device for bleeding compressed air by an air bleed duct () and a turbine () connected to the cabin () by a cabin inlet duct () in order to be able to supply said cabin with air at a controlled pressure and temperature, characterised in that it further comprises: stationary blading () which has a variable injection cross section and is mounted on said turbine () of said air cycle turbine engine () so as to be able to modify, on command, the flow rate and/or the pressure of air supplying an air inlet of said turbine (); and a second supercharger () which is mounted on said air cycle turbine engine () and is connected to a device for bleeding outside air and to said bleed duct.

Aircraft cabin environmental control system and method and aircraft equipped with such control system

The present disclosure relates to a method of operating an aircraft system, in particular for the purpose of fresh air supply, air-conditioning and pressurization of an aircraft cabin, having a first compressed air source formed by a first compressor charged with ambient air, ram air and/or precompressed air and driven by means of at least one motor and/or of at least one turbine and whose outlet is in direct or indirect communication with an aircraft cabin, said aircraft system having at least one second compressed air source whose outlet can be connected directly or indirectly to the aircraft cabin, wherein only the first compressed air source is in communication with the aircraft cabin in a first operating mode, wherein both the first and the second compressed air sources are in communication with the aircraft cabin in a second operating mode, and wherein the selection of the operating mode depends on the pressure of the ambient air such that the first operating mode is set at a high pressure of the ambient air and the second operating mode is set at a pressure of the ambient air lower in comparison.

Growing community of inventors

Bouloc, France

David Lavergne