-
公开(公告)号：US12065260B2
公开(公告)日：2024-08-20
申请号：US17878346
申请日：2022-08-01
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Alexis Pissavin , Lionel Czapla , Alistair Forbes
Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.
-
公开(公告)号：US12060851B2
公开(公告)日：2024-08-13
申请号：US18475570
申请日：2023-09-27
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Benjamin Thubert
Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.
-
公开(公告)号：US12018614B2
公开(公告)日：2024-06-25
申请号：US18356662
申请日：2023-07-21
Applicant: Airbus Operations SAS
Inventor： Pierre-Olivier Martin , Lionel Czapla , Mathieu Belleville
Abstract: A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.
-
公开(公告)号：US11867122B2
公开(公告)日：2024-01-09
申请号：US17963237
申请日：2022-10-11
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Jorge Alejandro Carretero Benignos , Lionel Czapla
CPC classification number: F02C7/16 , B64D27/12 , B64D29/06 , B64D33/08 , B64D37/32 , F02C7/22 , F02C9/46 , F05D2220/323 , F05D2240/35 , F05D2260/213 , F05D2270/09
Abstract: A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.
-
15.发明授权公开(公告)号：US11242821B2
公开(公告)日：2022-02-08
申请号：US17140717
申请日：2021-01-04
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Benjamin Thubert , Julien Le Fanic
Abstract: A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.
-
Patent Agency Ranking
16.发明授权公开(公告)号：US11215141B2
公开(公告)日：2022-01-04
申请号：US16431173
申请日：2019-06-04
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Lionel Czapla
Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.
-
公开(公告)号：US12296975B2
公开(公告)日：2025-05-13
申请号：US18602498
申请日：2024-03-12
Applicant: Airbus Operations SAS
Inventor： Lionel Czapla , Christophe Labarthe , Kotaro Fukasaku
Abstract: A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.
-
公开(公告)号：US12139267B2
公开(公告)日：2024-11-12
申请号：US17939000
申请日：2022-09-07
Applicant: Airbus Operations SAS
Inventor： Frédéric Piard , Lionel Czapla
Abstract: An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.
-
公开(公告)号：US11661203B2
公开(公告)日：2023-05-30
申请号：US17685608
申请日：2022-03-03
Applicant: Airbus Operations SAS
Inventor： Theophile Horde , Lionel Czapla , Christophe Labarthe
Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.
-
公开(公告)号：US11572189B2
公开(公告)日：2023-02-07
申请号：US16695375
申请日：2019-11-26
Applicant: Airbus Operations SAS
Inventor： Claire Maffre , Jérôme Gaillardo , Lionel Czapla , Florian Ravise , Laurent Caliman , Laurent Cazeaux , Antoine Cousin , Denis Brossard
IPC: F02K1/34 , F02C7/24 , G10K11/162 , G10K11/172
Abstract: An acoustic absorption structure comprising a plurality of resonators. Each resonator comprises a first chamber which has a first mouthpiece delimited by an edge pressed against an inner surface of a porous zone of a skin so that the first chamber and the skin delimit a first cavity, a second chamber, in which is positioned the first chamber, which delimits, with the first chamber, a second cavity, at least one acoustic orifice passing through the first chamber, at least one drainage orifice passing through the first chamber and at least one drainage hole passing the second chamber, each drainage orifice and each drainage hole being configured to limit an accumulation of fluid in the resonator. Also, an aircraft propulsive assembly or an aircraft comprising the acoustic absorption structure are provided.
-
-
-
-
-
-
-
-
-
Search Results
27
records
(took 0.012 seconds)
