Patents by Inventor David Lavergne
David Lavergne has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240136553Abstract: The invention relates to a supply device for compressed air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of compressed air to all of the cathodes (100a-100d), a group of ducts configured to conduct the compressed air to each cathode (100a-100d), for each cathode (100a-100d), a proportioning valve (20a-20d) upstream or downstream of said cathode (100a-100d) which is configured to regulate the flow rate of compressed air passing through said cathode (100a-100d), anti-pumping protection means (30, 32) configured to allow the flow of a minimum flow rate of compressed air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportioning valve (20a-20d) and/or the operation of the anti-pumping protection means (30, 32).Type: ApplicationFiled: February 22, 2022Publication date: April 25, 2024Applicant: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Karine PRINCE, David LAVERGNE, Cyril VAUCORET
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Patent number: 11958618Abstract: Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) 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 (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) 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.Type: GrantFiled: February 27, 2020Date of Patent: April 16, 2024Assignee: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Guillaume Galzin, Jean-Raymond Blary, David Lavergne
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Publication number: 20230402625Abstract: The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a cooling fluid circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating cooling air (26); a variable-speed pump (21) for supplying said cooling loop with cooling fluid as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of cooling fluid supplying this cell as a function of a measurement representative of the cooling need of this cell.Type: ApplicationFiled: October 25, 2021Publication date: December 14, 2023Applicant: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Karin PRINCE, David LAVERGNE
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Publication number: 20230391458Abstract: The invention relates to an air-conditioning system for an aircraft cabin (5) comprising: an engine air bleed device (10); an air-conditioning pack (20) comprising a pack air inlet (21) connected to said engine bleed device (10), and a pack air outlet (22) connected to said cabin (5); an auxiliary module (50) for supplying pressurized air comprising an auxiliary turbomachine (51), comprising a compressor (52) supplied with external fresh air and a turbine suitable to be able to be supplied with air coming from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with the pressurized air coming from the engine bleed device (10), or a fresh air mode in which said pack air inlet (21) is supplied with the pressurized air coming from the auxiliary module (50).Type: ApplicationFiled: October 26, 2021Publication date: December 7, 2023Applicant: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Frédéric SANCHEZ, Walid HANKACHE, David LAVERGNE, Cédric LANCE
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Publication number: 20230382537Abstract: System for protecting an outer surface of an aircraft comprising at least two fuel cells (112, 212) from icing, characterized in that it comprises a first and a third liquid circuit (114, 214) each causing a cooling liquid of the fuel cells (112, 212) to flow, a second and a fourth liquid circuit (118a, 118b) each causing an icing protection liquid to flow, at least two icing protection heat exchangers (120a-d, 220a-d) 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 (118a, 118b), and two liquid-liquid heat exchangers (116, 216) 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.Type: ApplicationFiled: October 6, 2021Publication date: November 30, 2023Applicant: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Karin PRINCE, David LAVERGNE
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Publication number: 20230187662Abstract: The invention relates to a system for cooling a fuel cell (10) of a transport vehicle such as an aircraft, comprising: a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by said fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into said dynamic air channel (40) upstream of said heat exchanger (30); and a computer (28) for controlling the amount of sprayed water on the basis of a measurement representing the temperature of said fuel cell (10).Type: ApplicationFiled: June 10, 2021Publication date: June 15, 2023Applicant: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Karine Prince, David Lavergne
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Patent number: 11577842Abstract: The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure airType: GrantFiled: October 5, 2018Date of Patent: February 14, 2023Assignee: LIEBHERR-AEROSPACE TOULOUSE SASInventors: David Lavergne, Fabrice Laborde, Julien Daumas, Patrick Favreau
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Publication number: 20220355938Abstract: The invention relates to an electrical air conditioning system for air conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) 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 (14) comprising at least a first compressor (15) and a first turbine (17) 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 (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet that can be connected either to a discharge port (54) 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 (10) orType: ApplicationFiled: June 16, 2020Publication date: November 10, 2022Inventors: David Lavergne, Frederic SANCHEZ
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Publication number: 20220194603Abstract: The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air. The air conditioning system comprises a network of pipes and associated valves, connected to the common outlet (24) of the compressors and making it possible to supply, from the common outlet of the compressors: either the inlet (160) of the water extraction turbine (16a), or the inlet (164) of the cooling turbine (16b), bypassing the turbine (16a) and the water extraction loop, or an outlet (60) of the air conditioning system directly, bypassing the cooling turbine (16b) and the water extraction turbine (16a).Type: ApplicationFiled: March 16, 2020Publication date: June 23, 2022Inventors: Frédéric SANCHEZ, David LAVERGNE, Vinciane MILLE
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Publication number: 20220048635Abstract: Air conditioning system for a cabin (10) of an aircraft, comprising: an air bleed device; an air cycle turbine engine (12); at least one main cooling exchanger (16); a water extraction loop (30); and a pipe (26) for distributing water extracted by said extraction loop (30), characterized in that said system further comprises means (40) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel (22) which supplies said main exchanger (16).Type: ApplicationFiled: February 27, 2020Publication date: February 17, 2022Inventors: Guillaume GALZIN, Jean-Raymond BLARY, David LAVERGNE
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Publication number: 20220048636Abstract: Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) 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 (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) 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.Type: ApplicationFiled: February 27, 2020Publication date: February 17, 2022Inventors: Guillaume GALZIN, Jean-Raymond BLARY, David LAVERGNE
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Patent number: 11046440Abstract: The invention relates to a system for environmental control of an aircraft cabin (5), comprising a device for bleeding compressed air from at least one aircraft engine; an air cycle turbine engine (20) comprising at least one supercharger (21) connected to said device for bleeding compressed air by an air bleed duct (7) and a turbine (22) connected to the cabin (5) by a cabin inlet duct (8) 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 (23) which has a variable injection cross section and is mounted on said turbine (22) of said air cycle turbine engine (20) 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 (22); and a second supercharger (22) which is mounted on said air cycle turbine engine (20) and is connected to a device for bleeding outside air and to said bleed duct.Type: GrantFiled: June 23, 2018Date of Patent: June 29, 2021Assignee: LIEBHERR-AEROSPACE TOULOUSE SASInventors: Fabrice Laborde, Cyril Vaucoret, Laurent Fayolle, David Lavergne
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Publication number: 20190185167Abstract: The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure airType: ApplicationFiled: October 5, 2018Publication date: June 20, 2019Inventors: David LAVERGNE, Fabrice Laborde, Jullen Daumas, Patrick Favreau
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Publication number: 20180370636Abstract: The invention relates to a system for environmental control of an aircraft cabin (5), comprising a device for bleeding compressed air from at least one aircraft engine; an air cycle turbine engine (20) comprising at least one supercharger (21) connected to said device for bleeding compressed air by an air bleed duct (7) and a turbine (22) connected to the cabin (5) by a cabin inlet duct (8) 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 (23) which has a variable injection cross section and is mounted on said turbine (22) of said air cycle turbine engine (20) 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 (22); and a second supercharger (22) which is mounted on said air cycle turbine engine (20) and is connected to a device for bleeding outside air and to said bleed duct.Type: ApplicationFiled: June 23, 2018Publication date: December 27, 2018Inventors: Fabrice Laborde, Cyril Vaucoret, Laurent Fayolle, David Lavergne
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Patent number: 7797962Abstract: 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 ambienType: GrantFiled: June 28, 2006Date of Patent: September 21, 2010Assignee: Liebherr-Aerospace Lindenberg GmbHInventors: Hubert Kresser, Markus Hirschmann, Alfred Sauterleute, David Lavergne, Laurent Hartenstein
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Publication number: 20090117840Abstract: 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 ambienType: ApplicationFiled: June 28, 2006Publication date: May 7, 2009Inventors: Hubert Kresser, Markus Hirschmann, Alfred Sauterleute, David Lavergne, Laurent Hartenstein