Liebherr-aerospace Toulouse Sas

Laurent Fayolle

Guillaume Galzin

Fabrice Laborde

David Lavergne

Cyril Vaucoret

Air conditioning system of an aircraft, comprising a thermal management system supplied with air, referred to as pressurized air (), by at least one compressor () of the aircraft, and supplied with non-pressurized flow air () from at least one engine of the aircraft, and characterized in that the thermal management system comprises: at least one pressurized-air/oil heat exchanger () designed to provide heat exchanges between a stream of pressurized air () and a first oil circuit (), allowing heat to be transferred from the pressurized air () to the oil of the first oil circuit (); at least one oil/flow-air heat exchanger () designed to provide heat exchanges between a second oil circuit () and the flow air (), allowing the heat from said second oil circuit () to be transferred to the flow air (); and at least one circuit () connecting the first oil circuit () and said second oil circuit ().

Air conditioning system equipped with a system for the thermal management of oil and of pressurized air

The invention relates to a system for cooling a fluid of a circuit () for lubricating a propulsion engine () of an aircraft, the engine comprising a nacelle () which extends in a longitudinal direction (X) between an air inlet opening () and an ejection nozzle (), a turbomachine () having a casing () secured inside said nacelle by rectifier arms (), and a fan () arranged at said air inlet opening () of said nacelle, upstream of said turbomachine (), and designed to be able to generate a primary air flow feeding said turbomachine and a secondary air flow feeding a channel, referred to as a secondary channel (), formed between said nacelle () and said casing () of said turbomachine, characterized in that said cooling system comprises a skin exchanger () which is arranged on an inner wall of said nacelle (), longitudinally between said air inlet opening () of said nacelle and said rectifier arms (), said skin exchanger being in fluid communication with said fluid circuit and designed to be able to provide heat exchanges between said lubricating fluid and the air flowing through said secondary channel.

System and method for cooling a fluid of a lubrication or cooling circuit of a drive unit of an aircraft, and aircraft propulsion engine provided with such a cooling system

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.

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Montrabe, France

Laurent Fayolle