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    HYBRID PROPULSION SYSTEM AND CONTROL METHOD THEREOF
    1.
    发明公开
    HYBRID PROPULSION SYSTEM AND CONTROL METHOD THEREOF 审中-公开

    公开(公告)号：EP3333401A1

    公开(公告)日：2018-06-13

    申请号：EP17205746.5

    申请日：2017-12-06

    申请人： Rolls-Royce North American Technologies, Inc.

    发明人： ARMSTRONG, Michael James

    IPC分类号： F02K3/00 ,  F02K5/00 ,  F02C9/58

    CPC分类号： B64D27/24 ,  B64D27/10 ,  B64D2027/026 ,  F02C9/58 ,  F02K3/00 ,  F02K5/00 ,  F04D29/362 ,  F05D2220/7642 ,  F05D2270/061 ,  H02K7/1823

    摘要： A system is described that includes a turbine engine including an engine fan including one or more variable-pitch blades driven by a shaft, which rotates at a rotational speed which depends on a pitch of the one or more variable-pitch blades of the engine fan. The system further includes a generator configured to produce alternating-current (AC) electricity at a particular frequency relative to the rotational speed of the shaft. The system also includes a propulsor, which includes a propulsor motor and a propulsor fan. The propulsor motor is configured to drive, based on the AC electricity produced by the generator, the propulsor fan. The system includes a controller configured to control the particular frequency of the AC electricity by at least controlling the pitch of the one or more variable-pitch blades of the engine fan and thereby the rotational speed of the generator.

    Integrated boost cavity ring generator for turbofan and turboshaft engines
    2.
    发明公开
    Integrated boost cavity ring generator for turbofan and turboshaft engines 审中-公开
    综合腔环发电机涡轮风扇和涡轮增压发动机

    公开(公告)号：EP1939406A3

    公开(公告)日：2014-02-26

    申请号：EP07122397.8

    申请日：2007-12-05

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Kern, John M. ,  Qu, Ronghai ,  Young, Craig Douglas

    IPC分类号： F01D15/10

    CPC分类号： F01D15/10 ,  F05D2220/76 ,  F05D2220/7642 ,  F05D2220/766 ,  F05D2220/768

    摘要： An electrical generator for extraction of electrical power from a gas turbine engine (10) includes a rotor portion (22) and a stator portion (24) disposed within a booster cavity (14) of the gas turbine engine (10). The rotor portion (22) is rotatably supported about the stator portion (24). The stator portion (24) rigidly is supported within the booster cavity (14). The rotor portion (22) has a plurality of poles circumferentially arranged opposite the stator portion (24). The stator portion (24) includes a plurality of coil portions (28) disposed about an outer periphery of the stator portion (24) adjacent to the stator portion (24). The stator (24) and rotor portions (22) are configured to generate electrical power when the rotor portion (22) is rotated about the stator portion (24) by a shaft of the gas turbine engine (10) to induce electrical currents in the coil portions (28). The electrical generator extracts electric power from the turbine engine to supplement primary electrical generation sources of the engine (10).

    AIRCRAFT ENGINE ASSEMBLY AND METHOD OF GENERATING ELECTRIC ENERGY FOR AN AIRCRAFT POWER SYSTEM
    8.
    发明公开
    AIRCRAFT ENGINE ASSEMBLY AND METHOD OF GENERATING ELECTRIC ENERGY FOR AN AIRCRAFT POWER SYSTEM 有权
    拉脱维亚革命联合会维和部队德黑兰ELEKTRISCHER ENERGIEFÜREIN LUFTFAHRZEUGVERSORGUNGSSYSTEM

    公开(公告)号：EP3023331A1

    公开(公告)日：2016-05-25

    申请号：EP15196006.9

    申请日：2015-11-24

    申请人： Hamilton Sundstrand Corporation

    发明人： PATEL, Dhaval ,  KOENIG, Andreas C. ,  SPIERLING, Todd A.

    IPC分类号： B64D33/00 ,  B64D41/00 ,  H02K19/18

    CPC分类号： F02C7/275 ,  B64D33/00 ,  B64D41/00 ,  B64D2221/00 ,  F02C3/04 ,  F02N11/04 ,  F05D2220/323 ,  F05D2220/7642 ,  H02K1/246 ,  H02K7/1823 ,  H02K19/20 ,  Y02T50/54

    摘要： An aircraft engine assembly includes an engine housing 32, a low pressure spool 24 disposed within the engine housing, and a high pressure spool 26 disposed within the engine housing. Also included is a flux-switching machine 40 disposed within the engine housing, the flux-switching machine comprising a rotor 42, a stator 44, a field winding 50 and an armature winding 52, the flux-switching machine configured to generate power for the aircraft power system. Also provided is a method of generating electric energy for an aircraft power system. The method includes energizing a field winding set of a flux-switching machine disposed entirely within an engine housing of the aircraft engine. The method also includes outputting electrical energy to an electrical system of the aircraft with a three phase armature winding of the flux-switching machine to provide electrical power to at least one aircraft component.

    摘要翻译： 飞机发动机组件包括发动机壳体32，设置在发动机壳体内的低压阀芯24和设置在发动机壳体内的高压阀芯26。 还包括设置在发动机壳体内的磁通切换机40，磁通切换机包括转子42，定子44，励磁绕组50和电枢绕组52，该磁通切换机被配置为产生用于 飞机电力系统。 还提供了一种为飞机动力系统产生电能的方法。 该方法包括对设置在飞机发动机的发动机壳体内的通量切换机的励磁绕组进行通电。 该方法还包括使用通量切换机的三相电枢绕组向飞行器的电气系统输出电能，以向至少一个飞行器部件提供电力。

    Electrical power generator for a gas turbine engine
    9.
    发明授权
    Electrical power generator for a gas turbine engine 有权
    Stromgeneratorfüreinen Gasturbinenmotor

    公开(公告)号：EP2910739B1

    公开(公告)日：2016-04-27

    申请号：EP15152873.4

    申请日：2015-01-28

    申请人： Rolls-Royce plc

    发明人： Edwards, Huw Llewelyn

    IPC分类号： H02P9/00 ,  F01D15/10 ,  F02C9/28 ,  H02P9/04 ,  H02P9/48

    CPC分类号： H02P9/04 ,  F01D15/10 ,  F02C6/20 ,  F02C9/00 ,  F02C9/28 ,  F05D2220/323 ,  F05D2220/764 ,  F05D2220/7642 ,  F05D2220/7646 ,  F05D2270/01 ,  F05D2270/02 ,  F05D2270/061 ,  F05D2270/071 ,  F05D2270/304 ,  F05D2270/309 ,  F05D2270/332 ,  F05D2270/335 ,  H02P9/007 ,  H02P9/48

    摘要： An electrical power generation system (100) for an aircraft gas turbine engine (10). The system comprises an alternating current electrical generator (110) having a rotor (114) comprising a plurality of electromagnetic rotor windings (118) and a stator (124) comprising a plurality of electrical stator windings (126). The rotor (114) is mechanically coupled to a shaft (36) of the gas turbine engine (10) by a transmission system (129). The electrical generator (110) further includes an electrical output frequency controller (130), a torque sensor arrangement configured to determine a torque imposed on the transmission system (129) by the generator (110) and a controller (112) configured to operate the electrical power generation system in first mode and second modes. In the first mode, the frequency of the electrical power output of the electrical generator (110) is controlled by the electrical output frequency controller (130) to lie within predetermined limits, and a reduced idle signal is provided to a gas turbine engine controller (132). In the second mode, the frequency of the electrical power output of the electrical generator (132) is not controlled by the electrical output frequency controller (130) and an increased idle signal is provided to the gas turbine engine controller (132). The electrical generator controller (112) is configured to operate the electrical power generation system (100) in the first mode when the torque is below a predetermined limit, and in the second mode when the torque is above a predetermined limit.

    摘要翻译： 一种用于飞机燃气涡轮发动机（10）的发电系统（100）。 该系统包括具有包括多个电磁转子绕组（118）和包括多个电定子绕组（126）的定子（124）的转子（114）的交流发电机（110）。 转子（114）通过传动系统（129）机械联接到燃气涡轮发动机（10）的轴（36）。 发电机（110）还包括电输出频率控制器（130），扭矩传感器装置被配置为确定由发电机（110）施加在传动系统（129）上的扭矩;以及控制器（112） 第一模式和第二模式下的发电系统。 在第一模式中，发电机（110）的电力输出的频率由电输出频率控制器（130）控制在预定的限度内，并且将降低的空闲信号提供给燃气涡轮发动机控制器 132）。 在第二模式中，发电机（132）的电力输出频率不受电输出频率控制器（130）的控制，并且向燃气涡轮发动机控制器（132）提供增加的空转信号。 发电机控制器（112）被配置为当转矩低于预定极限时在第一模式下操作发电系统（100），并且当扭矩高于预定极限时在第二模式中操作发电系统（100）。