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1.发明授权公开(公告)号：US08757542B2
公开(公告)日：2014-06-24
申请号：US13176846
申请日：2011-07-06
IPC分类号： B64D35/00
CPC分类号： B64D27/24 , B60L3/0046 , B60L3/0061 , B60L11/005 , B60L11/123 , B60L11/14 , B60L11/1853 , B60L2210/20 , B60L2240/36 , B60L2250/10 , B64C27/04 , B64C27/14 , B64D2027/026 , Y02T10/6217 , Y02T10/7005 , Y02T10/7022 , Y02T10/705 , Y02T10/7077 , Y02T10/725 , Y02T50/44 , Y02T50/64
摘要： A hybrid power plant (5) for an aircraft (1) comprises at least: a hybrid drive system (37) having a main on-board electricity network (16) and an auxiliary electricity network (34); and a selective adaptation interface (38) arranged to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks (16; 34). At least one engine and a hybrid drive auxiliary electrical machine (7, 31) are mechanically connected to a transmission (8); said machine (7) being electrically connected to at least one auxiliary electrical bus (36) in parallel with at least one auxiliary device for delivering electric charge.
摘要翻译： 一种用于飞机（1）的混合动力装置（5）至少包括：具有主车载电力网络（16）和辅助电力网络（34）的混合动力驱动系统（37）。 以及布置成使得能够在主电力网络和辅助电力网络（16; 34）之间有选择地交换电能的选择性适配接口（38）。 至少一个发动机和混合驱动辅助电机（7,31）机械连接到变速器（8）; 所述机器（7）与至少一个用于传送电荷的辅助装置并联地与至少一个辅助电气总线（36）电连接。
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2.发明申请公开(公告)号：US20120025032A1
公开(公告)日：2012-02-02
申请号：US13176846
申请日：2011-07-06
CPC分类号： B64D27/24 , B60L3/0046 , B60L3/0061 , B60L11/005 , B60L11/123 , B60L11/14 , B60L11/1853 , B60L2210/20 , B60L2240/36 , B60L2250/10 , B64C27/04 , B64C27/14 , B64D2027/026 , Y02T10/6217 , Y02T10/7005 , Y02T10/7022 , Y02T10/705 , Y02T10/7077 , Y02T10/725 , Y02T50/44 , Y02T50/64
摘要： A hybrid power plant (5) for an aircraft (1) comprises at least: a hybrid drive system (37) having a main on-board electricity network (16) and an auxiliary electricity network (34); and a selective adaptation interface (38) arranged to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks (16; 34). At least one engine and a hybrid drive auxiliary electrical machine (7, 31) are mechanically connected to a transmission (8); said machine (7) being electrically connected to at least one auxiliary electrical bus (36) in parallel with at least one auxiliary device for delivering electric charge.
摘要翻译： 一种用于飞机（1）的混合动力装置（5）至少包括：具有主车载电力网络（16）和辅助电力网络（34）的混合动力驱动系统（37）。 以及布置成使得能够在主电力网络和辅助电力网络（16; 34）之间有选择地交换电能的选择性适配接口（38）。 至少一个发动机和混合驱动辅助电机（7,31）机械连接到变速器（8）; 所述机器（7）与至少一个用于传送电荷的辅助装置并联地与至少一个辅助电气总线（36）电连接。
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3.发明授权Device and a method for starting a turbine engine fitted to a helicopter, making use of an electrical energy source that includes discharge booster members 有权装置和一种用于起动安装在直升机上的涡轮发动机的方法，利用包括放电增压部件的电能源公开(公告)号：US08752392B2
公开(公告)日：2014-06-17
申请号：US12816608
申请日：2010-06-16
IPC分类号： F02C7/268
CPC分类号： F02C7/26 , F02C7/268 , F05D2220/329 , F05D2260/85 , Y02T50/671
摘要： The invention provides a device and a method for starting at least one turbine engine (1) fitted to a helicopter. A starter (6) is fed with electrical energy from an electricity network (8) including at least one battery (9) and/or an electrical energy generator member. Discharge members (10) suitable for providing the starter (6) with a short-term boost of electrical energy in the form of a high-power pulse are incorporated in the network (8). The current pulse is delivered at a determined instant T starting from when the starter (6) is itself started, and/or from a determined threshold S for the speed and/or the variation in the speed with which the compressor (2) of the turbine engine (1) is driven, and/or from detecting D the ignition stage of the turbine engine (1), and/or from a manual control.
摘要翻译： 本发明提供一种用于启动装配到直升机的至少一个涡轮发动机（1）的装置和方法。 起动器（6）从包括至少一个电池（9）和/或电能发生器构件的电网（8）馈送电能。 适于提供起动器（6）的大功率脉冲形式的电能的短期升压的放电构件（10）被并入网络（8）中。 当起动器（6）自身起动时，从起动器（6）起动的确定时刻T和/或来自确定的速度和/或速度的变化的确定的阈值S来传送当前脉冲。 涡轮发动机（1）被驱动，和/或从涡轮发动机（1）的点火级检测D和/或来自手动控制。
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4.发明申请DEVICE AND A METHOD FOR STARTING A TURBINE ENGINE FITTED TO A HELICOPTER, MAKING USE OF AN ELECTRICAL ENERGY SOURCE THAT INCLUDES DISCHARGE BOOSTER MEMBERS 有权装置和用于启动直升机的涡轮发动机的方法，使用包括放电增压器构件的电能源公开(公告)号：US20100319357A1
公开(公告)日：2010-12-23
申请号：US12816608
申请日：2010-06-16
IPC分类号： F02C7/26
CPC分类号： F02C7/26 , F02C7/268 , F05D2220/329 , F05D2260/85 , Y02T50/671
摘要： The invention provides a device and a method for starting at least one turbine engine (1) fitted to a helicopter. A starter (6) is fed with electrical energy from an electricity network (8) including at least one battery (9) and/or an electrical energy generator member. Discharge members (10) suitable for providing the starter (6) with a short-term boost of electrical energy in the form of a high-power pulse are incorporated in the network (8). The current pulse is delivered at a determined instant T starting from when the starter (6) is itself started, and/or from a determined threshold S for the speed and/or the variation in the speed with which the compressor (2) of the turbine engine (1) is driven, and/or from detecting D the ignition stage of the turbine engine (1), and/or from a manual control.
摘要翻译： 本发明提供一种用于启动装配到直升机的至少一个涡轮发动机（1）的装置和方法。 起动器（6）从包括至少一个电池（9）和/或电能发生器构件的电网（8）馈送电能。 适于提供起动器（6）的大功率脉冲形式的电能的短期升压的放电构件（10）被并入网络（8）中。 当起动器（6）自身起动时，从起动器（6）起动的确定时刻T和/或来自确定的速度和/或速度的变化的确定的阈值S来传送当前脉冲。 涡轮发动机（1）被驱动，和/或从涡轮发动机（1）的点火级检测D和/或来自手动控制。
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