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公开(公告)号：US20230406530A1
公开(公告)日：2023-12-21
申请号：US18335224
申请日：2023-06-15
发明人： Romain JOUBERT , Lionel CZAPLA , Jérôme MILLIERE
摘要： 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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公开(公告)号：US20230167770A1
公开(公告)日：2023-06-01
申请号：US17963237
申请日：2022-10-11
申请人： Airbus SAS , Airbus Operations SAS
CPC分类号： F02C7/16 , F02C7/22 , F02C9/46 , B64D27/12 , B64D29/06 , B64D33/08 , B64D37/32 , F05D2220/323 , F05D2240/35 , F05D2260/213 , F05D2270/09
摘要： 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.
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公开(公告)号：US20230084689A1
公开(公告)日：2023-03-16
申请号：US17939000
申请日：2022-09-07
发明人： Frédéric PIARD , Lionel CZAPLA
摘要： 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.
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公开(公告)号：US20230043843A1
公开(公告)日：2023-02-09
申请号：US17878346
申请日：2022-08-01
申请人： Airbus SAS , Airbus Operations SAS
发明人： Alexis PISSAVIN , Lionel CZAPLA , Alistair FORBES
摘要： 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.
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公开(公告)号：US20220355942A1
公开(公告)日：2022-11-10
申请号：US17734212
申请日：2022-05-02
发明人： Pascal POME , Lionel CZAPLA , Benjamin THUBERT
IPC分类号： B64D27/24
摘要： A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.
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公开(公告)号：US20220289396A1
公开(公告)日：2022-09-15
申请号：US17685608
申请日：2022-03-03
摘要： 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.
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37.发明申请公开(公告)号：US20190309704A1
公开(公告)日：2019-10-10
申请号：US16371430
申请日：2019-04-01
发明人： Frédéric RIDRAY , Lionel CZAPLA , Frédéric PIARD
摘要： A ducted fan turbojet including a nacelle including a fixed structure, a thrust reverser system having a frame, a mobile structure fastened to the frame, inner doors and outer doors hinged at the frame. The frame is mobile in translation on the fixed structure between a forward position and a rear position so as to define a window between the fixed structure and the mobile structure, the window being open between a bypass duct and the exterior of the nacelle. Each door is mobile between a stowed position and a deployed position and the mobile structure is assembled hinged on the frame via at least one hinge whose axis of rotation is globally parallel to a longitudinal axis of the ducted fan turbojet.
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