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公开(公告)号：US20240110536A1
公开(公告)日：2024-04-04
申请号：US18475570
申请日：2023-09-27
发明人： Lionel CZAPLA , Benjamin THUBERT
CPC分类号： F02K3/04 , B64D29/02 , B64D29/06 , F05D2220/36
摘要： 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.
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公开(公告)号：US20240067354A1
公开(公告)日：2024-02-29
申请号：US18456586
申请日：2023-08-28
发明人： Lionel CZAPLA , Emmanuel VARDELLE
摘要： 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：US20230045036A1
公开(公告)日：2023-02-09
申请号：US17878331
申请日：2022-08-01
申请人： Airbus SAS , Airbus Operations SAS
发明人： Lionel CZAPLA , Antoine ABELE , Benjamin THUBERT , Alexis PISSAVIN , Abhishek VERMA , Alistair FORBES , Jorge A. CARRETERO BENIGNOS , Benedikt BAMMER
摘要： 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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4.发明申请公开(公告)号：US20190383172A1
公开(公告)日：2019-12-19
申请号：US16424650
申请日：2019-05-29
发明人： Thierry GACHES , Lionel CZAPLA , Bastian SABATHIER
摘要： A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.
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公开(公告)号：US20240317419A1
公开(公告)日：2024-09-26
申请号：US18608140
申请日：2024-03-18
申请人： Airbus SAS , Airbus Operations SAS
发明人： Jérôme MILLIERE , Lionel CZAPLA , Alexis PISSAVIN
摘要： A module between a dihydrogen tank and an engine in an aircraft. The module comprises outer and inner boxes, a pipeline between the tank and the engine through the boxes, pressure limiters mounted on the pipeline and the inner box, an exhaust pipeline between the pressure limiters and the outside, shut-off valves mounted on the pipeline at the outer box, a detector for detecting a leak of the pipeline or of the outer box and a controller configured to control each shut-off valve as a function of the information delivered by the detector.
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公开(公告)号：US20240109668A1
公开(公告)日：2024-04-04
申请号：US18476586
申请日：2023-09-28
申请人： Airbus SAS , Airbus Operations SAS
发明人： Philippe MOGILKA , Lionel CZAPLA , Alexis PISSAVIN
摘要： 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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7.发明申请公开(公告)号：US20200025141A1
公开(公告)日：2020-01-23
申请号：US16431173
申请日：2019-06-04
发明人： Pascal GARDES , Frédéric RIDRAY , Lionel CZAPLA
摘要： 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.
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公开(公告)号：US20190003421A1
公开(公告)日：2019-01-03
申请号：US16017634
申请日：2018-06-25
摘要： A turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.
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公开(公告)号：US20180346138A1
公开(公告)日：2018-12-06
申请号：US15984622
申请日：2018-05-21
发明人： Frédéric RIDRAY , Lionel CZAPLA , Frédéric PIARD
摘要： A propulsion system comprising a pylon, a turbomachine with a core and a nacelle. The nacelle comprises two inner cowls and two outer cowls around the inner cowls, where each outer cowl is mounted articulated via hinges and is mobile between a closed position in which the outer cowl is tightened around the core and an open position in which the outer cowl is separated from the core. Furthermore, each inner cowl is mounted articulated on the pylon via fixed hinges and is mobile between a closed position in which the inner cowl is tightened around the core and an open position in which the inner cowl is separated from the core. The placement of the hinges between the pylon and each inner cowl makes it possible to separate the rotation of the inner cowl from the rotation of the associated outer cowl.
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公开(公告)号：US20240327023A1
公开(公告)日：2024-10-03
申请号：US18602498
申请日：2024-03-12
摘要： 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.
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