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    PROCÉDÉ ET ARCHITECTURE DE TRANSFERT D'ÉNERGIE OPTIMISÉ ENTRE UN MOTEUR AUXILIAIRE DE PUISSANCE ET LES MOTEURS PRINCIPAUX D'UN HELICOPTERE
    1.
    发明公开
    PROCÉDÉ ET ARCHITECTURE DE TRANSFERT D'ÉNERGIE OPTIMISÉ ENTRE UN MOTEUR AUXILIAIRE DE PUISSANCE ET LES MOTEURS PRINCIPAUX D'UN HELICOPTERE 审中-公开
    方法和系统能量传递主要和辅助驱动器之间在直升机

    公开(公告)号：EP2861493A1

    公开(公告)日：2015-04-22

    申请号：EP13733392.8

    申请日：2013-06-12

    申请人： Turbomeca ,  Microturbo

    发明人： DAURIAC, Pascal ,  BEDRINE, Olivier ,  MARCONI, Patrick ,  RIDEAU, Jean-François

    IPC分类号： B64D35/08

    CPC分类号： B64D35/08 ,  B64D41/00 ,  B64D2041/002 ,  F02C6/02 ,  F02C7/277 ,  F05D2220/329 ,  Y02T50/53

    摘要： The aim of the invention is to optimize the entirety of the drive power available in a helicopter by using an auxiliary motor to supply power to the equipment and accessories of the helicopter that are connected to the engines. In an example of an optimized power transfer architecture for implementing the invention, the main engines (1, 1') and the APU group (8), as an auxiliary motor, comprise a gas generator (2; 81) connected, for the main engines (1, 1'), to the gearboxes (6) and accessory boxes (7) of mechanical, electric, and/or hydraulic power sockets, and connected, for the APU group (8), to at least one power conversion member (83, 84, 11). The power conversion member (83, 84, 11) of the APU group (8) is connected to the equipment and accessories via the gearbox (6) and/or via the accessory box (7) of the main engines (1, 1').

    摘要翻译： 的方法和体系结构通过使用辅助发动机的将能量提供给设备和连接到所述发动机的直升机的配件，以优化在直升机上可用的整个系统上的牵引力。 主发动机和在APU单元，作为辅助发动机，包括连接到气体发生器，对于主发动机，减速齿轮箱和用于机械，电气和/或液压动力输出附件齿轮箱和连接到，对于 APU单元，至少一个电力转换构件。 APU装置的功率转换部件由所述减速齿轮箱和/或所述主发动机的附件齿轮箱连接到所述的设备和附件。

    DISPOSITIF D'ALIMENTATION ÉLECTRIQUE D'UN AÉRONEF AU SOL
    2.
    发明公开
    DISPOSITIF D'ALIMENTATION ÉLECTRIQUE D'UN AÉRONEF AU SOL 有权
    设备与电力对隧道地面的飞行器供应

    公开(公告)号：EP2740191A2

    公开(公告)日：2014-06-11

    申请号：EP12753762.9

    申请日：2012-07-27

    申请人： Hispano Suiza ,  Turbomeca

    发明人： VIEILLARD, Sébastien ,  BERENGER, Serge ,  ROQUES, Serge, Thierry ,  DAURIAC, Pascal

    IPC分类号： H02J4/00 ,  B64C25/40

    CPC分类号： B64C25/405 ,  B64D41/00 ,  H02J4/00 ,  Y02T50/44 ,  Y02T50/823

    摘要： The invention relates to a device (210) for supplying an aircraft on the ground with electricity, comprising two electric generators (216, 218) driven by an auxiliary power unit (220), characterized in that the first generator is connected by connection/disconnection means (232) to an aircraft network (212) and to an electrical taxiing network (214), so as to either provide an AC voltage Vac2 to the aircraft network when it is connected to this network, or to provide an AC voltage Vac1 or power P to the taxiing network when it is connected to this network, and in that the second generator is connected by connection/disconnection means (232) to the aircraft network (212) so as to provide this network with an AC voltage Vac2 only when the first generator is supplying the taxiing network.