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公开(公告)号：US12292001B2
公开(公告)日：2025-05-06
申请号：US18476586
申请日：2023-09-28
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Philippe Mogilka , Lionel Czapla , Alexis Pissavin
Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.
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公开(公告)号：US12291340B2
公开(公告)日：2025-05-06
申请号：US17849895
申请日：2022-06-27
Applicant: Airbus Operations SAS , Airbus SAS
Inventor： Pascal Pome , Nicolas Jolivet , Rémi Amargier , Lionel Czapla , Franck Alvarez , Kotaro Fukasaku , Benoît Penven , Delphine Jalbert , Laurent Lafont , Milan Tasic , Frédéric Goupil , Jean-Victor Lapeyre , Emmanuel Mermoz
Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.
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公开(公告)号：US11840962B2
公开(公告)日：2023-12-12
申请号：US17878331
申请日：2022-08-01
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Lionel Czapla , Antoine Abele , Benjamin Thubert , Alexis Pissavin , Abhishek Verma , Alistair Forbes , Jorge A. Carretero Benignos , Benedikt Bammer
CPC classification number: F02C7/224 , B64D37/04 , B64D37/30 , B64D37/34 , F02C3/22 , F02C7/222 , F02C9/40 , F05D2220/323 , F05D2260/213 , F05D2260/232 , F05D2260/606
Abstract: An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.
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公开(公告)号：US12291350B2
公开(公告)日：2025-05-06
申请号：US18456586
申请日：2023-08-28
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Emmanuel Vardelle
Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.
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公开(公告)号：US12104554B2
公开(公告)日：2024-10-01
申请号：US18484548
申请日：2023-10-11
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Benjamin Thubert
Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.
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Patent Agency Ranking
公开(公告)号：US12078428B2
公开(公告)日：2024-09-03
申请号：US17879869
申请日：2022-08-03
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Lionel Czapla , Jorge A. Carretero Benignos
CPC classification number: F28D9/0006 , B64D37/32 , B64D37/34 , F02C7/224 , F28D9/0037 , F28F3/005 , F28F9/005 , F28F2265/16
Abstract: A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.
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公开(公告)号：US11975858B2
公开(公告)日：2024-05-07
申请号：US17971680
申请日：2022-10-24
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Frédéric Piard
IPC: B64D29/00
CPC classification number: B64D29/00
Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.
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公开(公告)号：US11519362B2
公开(公告)日：2022-12-06
申请号：US17140707
申请日：2021-01-04
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Benjamin Thubert , Julien Le Fanic
Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.
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公开(公告)号：US11348565B2
公开(公告)日：2022-05-31
申请号：US16664995
申请日：2019-10-28
Applicant: Airbus Operations SAS
Inventor： Florian Ravise , Lionel Czapla
IPC: G10K11/168 , G10K11/172 , B32B3/12 , B32B3/26
Abstract: An assembly forming an acoustic insulator having a first sheet, a pierced second sheet, and a plurality of first and second structures. Each first structure comprises a first and a second strip, wherein each is shaped to form half of the wall of a cage and wherein, for two successive halves, each strip comprises a facet of a joining wall. Each second structure is made up of a first and a second strip, wherein each is shaped to form half of the wall of a cone, wherein. For each strip, at least one of the wall halves of each cone is pierced. For two successive halves, each strip comprises one facet of the connecting wall. Each cone is located in a cell and each connecting wall is located between the two facets of a joining wall, and, between two adjacent first structures, a second structure is likewise fitted.
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公开(公告)号：US12246848B2
公开(公告)日：2025-03-11
申请号：US18335224
申请日：2023-06-15
Applicant: Airbus Operations SAS
Inventor： Romain Joubert , Lionel Czapla , Jérôme Milliere
Abstract: A casing system mounted between an upstream solenoid valve of an upstream pipe and a downstream solenoid valve of a downstream pipe and which has a casing divided by a separation wall into a first volume which is placed under reduced pressure and a second volume, a heat exchanger which is fixed inside the casing with a first inlet which is arranged in the first volume and which is connected to the upstream pipe and a first outlet which is arranged in the second volume and which is connected to the downstream pipe, and a control unit which closes the solenoid valves if the deviation between two successive values of the pressure in the first volume or in the second volume is greater than a threshold.
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