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103 条记录 (耗时 0.017 秒)

    CRYOGENIC FUELED AIRCRAFT
    1.
    发明公开
    CRYOGENIC FUELED AIRCRAFT 审中-公开

    公开(公告)号：EP4438489A1

    公开(公告)日：2024-10-02

    申请号：EP24163125.8

    申请日：2024-03-13

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64D37/04 ,  B64D37/30 ,  B64D27/12 ,  B64D27/18

    CPC分类号： B64D37/30 ,  B64D37/04 ,  B64D27/18 ,  B64D27/12

    摘要： A hydrogen fuelled aircraft comprises a fuselage, a wing, at least one hydrogen fuelled gas turbine engine, at least one hydrogen fuel tank configured to store liquid or supercritical hydrogen and a hydrogen fuel line configured to delivery hydrogen fuel from the fuel tank to the engine. The gas turbine engine and the hydrogen fuel tank are each installed externally on the wing, and the hydrogen fuel line does not pass through the fuselage.

    GAS TURBINE ENGINE MOUNTED ABOVE WING AND WITH CAMBER
    3.
    发明公开
    GAS TURBINE ENGINE MOUNTED ABOVE WING AND WITH CAMBER 审中-公开

    公开(公告)号：EP3992084A1

    公开(公告)日：2022-05-04

    申请号：EP21205765.7

    申请日：2021-11-01

    申请人： Raytheon Technologies Corporation

    发明人： MALECKI, Robert E. ,  HAHN, Andrew ,  MULDOON, Marc J. ,  STAUBACH, Joseph B. ,  CHANDLER, Jesse M.

    IPC分类号： B64D27/02 ,  B64D27/12 ,  B64D29/02

    摘要： A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation (X). An outer nacelle (106A) surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle (106A) is formed with camber (122) so as to be curved in a first plane away from the axis of rotation (X) in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction.

    ENSEMBLE POUR UN AERONEF, LEDIT ENSEMBLE COMPORTANT UN MAT ET UNE AILE
    4.
    发明公开
    ENSEMBLE POUR UN AERONEF, LEDIT ENSEMBLE COMPORTANT UN MAT ET UNE AILE 审中-公开

    公开(公告)号：EP3984888A1

    公开(公告)日：2022-04-20

    申请号：EP21202735.3

    申请日：2021-10-14

    申请人： AIRBUS OPERATIONS

    发明人： MESSINA, Paolo ,  PAUTIS, Olivier

    IPC分类号： B64D27/12 ,  B64D27/18 ,  B64D27/26

    摘要： L'invention concerne un ensemble (200) comportant un mât (106) avec un longeron supérieur (202) et quatre pelles latérales (212a), une aile avec une peau (210), des longerons longitudinaux (206a-b) et des ferrures (208), et pour chaque pelle latérale (212a), deux ensembles de fixation (250), où la peau (210) et la ferrure (208) comportent chacune un premier alésage (251) et où le longeron supérieur (202) et la pelle latérale (212a) comportent chacun un deuxième alésage (253), où chaque ensemble de fixation (250) comporte une vis (254) traversant les premiers et les deuxièmes alésages (251, 253), un écrou (255), deux bagues excentriques (256, 258), enfilées l'une sur l'autre et sur la vis (254), et un système d'arrêt en rotation (260) des bagues excentriques (256, 258).
    L'ensemble permet de s'affranchir de l'utilisation des spigots tout en assurant la reprise des efforts de cisaillement contenus dans le plan XY par les boulons du fait des tolérances réduites entre les différents alésages (251,253), les surfaces externes et internes des bagues excentriques (256, 258) et les zones lisses des vis (254).

    SYSTEMS AND METHODS FOR AIRCRAFT WING PLUG
    6.
    发明公开
    SYSTEMS AND METHODS FOR AIRCRAFT WING PLUG 审中-公开

    公开(公告)号：EP3912904A1

    公开(公告)日：2021-11-24

    申请号：EP21174523.7

    申请日：2021-05-18

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： BERTRAND, Pierre ,  THOMASSIN, Jean

    IPC分类号： B64C3/32 ,  B64D27/02 ,  B64D27/06 ,  B64D27/12 ,  B64D27/18 ,  B64D27/24 ,  B64F5/00

    摘要： The aircraft includes a fuselage (12) and at least one wing (14, 16) extending from the fuselage. The wing includes first and second original portions (102, 104) and a plug portion (106) positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant (110) and at least one combustion powerplant (112). Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion. A method for retrofitting an aircraft includes segmenting a wing of an aircraft into two original portions, positioning a plug portion between the two original portions, and connecting the plug portion to one of the two original portions, the first nacelle and/or the second nacelle.

    SUPERSONIC JET AIRCRAFT
    8.
    发明公开
    SUPERSONIC JET AIRCRAFT 审中-公开

    公开(公告)号：EP3650342A1

    公开(公告)日：2020-05-13

    申请号：EP19199194.2

    申请日：2019-09-24

    申请人： Rolls-Royce plc

    发明人： Hales, Michael ,  Bradbrook, Stephen

    IPC分类号： B64C30/00 ,  B64D31/06 ,  B64D27/12 ,  B64D27/14 ,  B64D33/02

    摘要： A supersonic jet aircraft and a method of operating the same. The supersonic jet aircraft having at least three turbofan engines and an engine management computer. A first engine of the at least three turbofan engines is configured to be de-activatable during flight to move from an operational state in which it provides thrust to an operational state in which it stops providing thrust. Other engines of the at least three turbofan engines are configured to provide sufficient thrust to the supersonic jet aircraft when the first engine is de-activated such that the aircraft can perform a supersonic climb operation and/or a supersonic cruise operation.