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    SYSTEMS FOR GENERATING AUXILLARY ELECTRICAL POWER FOR JET AIRCRAFT PROPULSION SYSTEMS
    1.
    发明申请
    SYSTEMS FOR GENERATING AUXILLARY ELECTRICAL POWER FOR JET AIRCRAFT PROPULSION SYSTEMS 审中-公开
    用于喷气飞机推进系统的辅助电力系统

    公开(公告)号：WO2015073101A3

    公开(公告)日：2015-07-09

    申请号：PCT/US2014053190

    申请日：2014-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AKIN JOHN

    IPC: H01L35/30

    CPC classification number: B64D33/00 ,  B64D27/16 ,  B64D2221/00 ,  F02C7/00 ,  H01L35/02 ,  H01L35/30 ,  H02K7/1823 ,  Y02T50/671

    Abstract: An aircraft jet propulsion system is disclosed. The aircraft jet propulsion system may comprise a thermoelectric generator array ("TEG" array) coupled to a portion of the aircraft jet propulsion system, wherein the TEG array converts heat energy to electrical energy, and supplies power to the aircraft jet propulsion system, wherein the electrical energy is supplied to a power supply. The aircraft jet propulsion system may comprise an alternator that generates less energy than is required to power the aircraft jet propulsion system. The TEG array may supplement the energy generated by the alternator. The energy generated by the TEG array and the energy generated by the alternator may be sufficient to power the aircraft jet propulsion system and/or the electrical energy generated by the TEG array may be sufficient to power to aircraft jet propulsion system.

    Abstract translation: 公开了一种飞机喷气推进系统。 飞机喷气推进系统可以包括耦合到飞机喷气推进系统的一部分的热电发电机阵列（“TEG”阵列），其中TEG阵列将热能转换成电能并且向飞机喷气推进系统供电，其中 电能被提供给电源。 飞机喷气推进系统可以包括交流发电机，其产生的能量比驱动飞机喷气推进系统所需的能量少。 TEG阵列可以补充交流发电机产生的能量。 由TEG阵列产生的能量和由交流发电机产生的能量可足以为飞机喷射推进系统提供动力和/或由TEG阵列产生的电能可足以为飞机喷射推进系统提供动力。

    NACELLE SCOOP INLET
    2.
    发明申请
    NACELLE SCOOP INLET 审中-公开

    公开(公告)号：WO2014077922A3

    公开(公告)日：2014-07-31

    申请号：PCT/US2013055935

    申请日：2013-08-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H

    IPC: F02C7/04 ,  B64D33/00

    CPC classification number: B64D33/00 ,  B64D29/00 ,  B64D33/08 ,  B64D2033/024 ,  F02C7/04 ,  F02C7/12 ,  F02C9/18 ,  Y02T50/675 ,  Y10T137/0536

    Abstract: A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the scoop inlet. A nacelle and a gas turbine engine are also disclosed.

    Abstract translation: 用于燃气轮机发动机舱的铲斗入口具有铲斗入口和从铲斗入口向前延伸的翼片。 瓢与下游流路相通。 标签在舀勺入口的上游位置至少有一个开口。 还公开了机舱和燃气涡轮发动机。

    AIRCRAFT POWER DISTRIBUTION NETWORK
    3.
    发明申请
    AIRCRAFT POWER DISTRIBUTION NETWORK 审中-公开
    飞机功率分配网络

    公开(公告)号：WO2012038266A3

    公开(公告)日：2012-12-13

    申请号：PCT/EP2011065581

    申请日：2011-09-08

    Applicant: AIRBUS OPERATIONS LTD ,  AIRBUS OPERATIONS GMBH ,  TODD TIMOTHY ,  NITSCHE THORSTEN

    Inventor： TODD TIMOTHY ,  NITSCHE THORSTEN

    IPC: H02J4/00

    CPC classification number: B64D33/00 ,  B64D2221/00 ,  H02J4/00 ,  H02J9/061 ,  H02J2009/068

    Abstract: An aircraft power distribution network comprising first 8 and second 9 galvanically isolated power bus bars, and first 7a and second 7b remote data concentrators (RDCs), each RDC having an input/output interface (I/O) 12 and a power supply 11, the first RDC power supply being connected to the first power bus bar, the second RDC power supply being connected to the second power bus bar, an input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to supply electrical power to the input/output device 14 through its respective I/O, wherein each RDC includes a switch 15 for isolating the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output device by both RDCs simultaneously. Also, a method of operating the network.

    Abstract translation: 一种包括第一8和第二隔离电源母线9以及第一7a和第二7b远程数据集中器（RDC）的飞机配电网，每个RDC具有输入/输出接口（I / O）12和电源11， 所述第一RDC电源连接到所述第一电力总线，所述第二RDC电源连接到所述第二电力总线条，输入/输出装置连接到所述第一RDC的I / O和所述I / O 的每个RDC适于通过其相应的I / O向输入/输出设备14提供电力，其中每个RDC包括用于隔离输入/输出设备的开关15，并且可操作地耦合的开关使得 两个RDC不能同时向输入/输出设备供电。 另外，操作网络的方法。

    AIRCRAFT POWER DISTRIBUTION NETWORK
    4.
    发明申请
    AIRCRAFT POWER DISTRIBUTION NETWORK 审中-公开
    飞机功率分配网络

    公开(公告)号：WO2012038266A2

    公开(公告)日：2012-03-29

    申请号：PCT/EP2011/065581

    申请日：2011-09-08

    Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS GMBH ,  TODD, Timothy ,  NITSCHE, Thorsten

    Inventor： TODD, Timothy ,  NITSCHE, Thorsten

    IPC: H02J4/00

    CPC classification number: B64D33/00 ,  B64D2221/00 ,  H02J4/00 ,  H02J9/061 ,  H02J2009/068

    Abstract: An aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the first RDC power supply being connected to the first power bus bar, the second RDC power supply being connected to the second power bus bar, an input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to supply electrical power to the input/output device through its respective I/O, wherein each RDC includes a switch for isolating the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output device by both RDCs simultaneously. Also, a method of operating the network.

    Abstract translation: 一种包括第一和第二电隔离电力汇流条以及第一和第二远程数据集中器（RDC）的飞机配电网，每个RDC具有输入/输出接口（I / O）和电源，所述第一RDC电源为 连接到第一电源母线，第二RDC电源连接到第二电源母线，输入/输出装置连接到第一RDC的I / O和第二RDC的I / O，每个 RDC适于通过其相应的I / O向输入/输出设备提供电力，其中每个RDC包括用于隔离输入/输出设备的开关，并且开关被可操作地耦合，使得电力不能被提供给输入 /输出设备同时由两个RDC。 另外，操作网络的方法。

    EMBEDDED ELECTRIC MACHINE
    6.
    发明申请
    EMBEDDED ELECTRIC MACHINE 审中-公开
    嵌入式电机

    公开(公告)号：WO2018067231A2

    公开(公告)日：2018-04-12

    申请号：PCT/US2017/046190

    申请日：2017-08-10

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： KUPISZEWSKI, Thomas ,  MILLER, Brandon Wayne ,  VONDRELL, Randy M. ,  GEMIN, Paul Robert

    CPC classification number: B64D27/12 ,  B64C21/06 ,  B64D27/18 ,  B64D27/24 ,  B64D29/04 ,  B64D33/00 ,  B64D2027/026 ,  B64D2033/0226 ,  B64D2221/00 ,  F01D9/065 ,  F01D15/10 ,  F01D25/162 ,  F02C3/04 ,  F02C7/16 ,  F02C7/32 ,  F02K5/00 ,  F04D25/06 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2260/20 ,  F05D2260/98 ,  Y02T50/676

    Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.

    Abstract translation: 燃气涡轮发动机包括共同限定核心空气流动路径的压缩机部分和涡轮部分。 此外，旋转部件可与压缩机部分的至少一部分和涡轮部分的至少一部分一起旋转。 电机与旋转部件同轴地安装并且沿着燃气涡轮发动机的径向方向至少部分地定位在核心空气流动路径的内部。 电气通信总线电连接到电机并且延伸穿过核心空气流动路径以例如将电机电连接到燃气涡轮发动机或包括燃气涡轮发动机的推进系统的一个或多个系统。

    유체흐름을 이용한 추진기구
    7.
    发明申请
    유체흐름을 이용한 추진기구 审中-公开
    使用流体流动的推进装置

    公开(公告)号：WO2014021653A1

    公开(公告)日：2014-02-06

    申请号：PCT/KR2013/006933

    申请日：2013-08-01

    Applicant: 김낙회

    Inventor： 김낙회

    IPC: B64C3/00 ,  B63B1/16 ,  B63H9/00

    CPC classification number: B64D27/02 ,  B63B1/248 ,  B63H1/26 ,  B63H1/265 ,  B64C21/04 ,  B64C23/06 ,  B64D29/02 ,  B64D33/00 ,  Y02T50/162 ,  Y02T50/166

    Abstract: 본 발명은 유체흐름을 이용한 추진기구에 관한 것으로, 더욱 상세하게는 추진기구 상면에 발생하는 와류를 외측으로 배출하면서, 추가된 유체공급부를 통해 유입되는 유체량을 증대시켜 상기 와류 발생 및 배출속도를 더 향상시켜, 추진기구가 장치된 제품의 항력을 개선하고 추력을 향상시킬 수 있도록 발명된 것이다. 본 발명의 구성은, 유체가 유입되는 전방의 제1유입선(11)과 유체가 유출되는 후방의 제1유츌선 (12)사이에 하부로 곡면진 유체저장면(13)을 형성하여 유체저장면(13) 상부에 유체저장공간(14)을 조성하고, 상기 유체저장면(13) 일측에 격벽(15)을 형성한 유체저장부(10)와; 상기 제1유입선(11) 단부에 제2유입선(21)을 외측 후방으로 경사지게 형성하고, 상기 제1유출선(12) 단부에 연접된 제2유출선(22)을 외측 후방으로 경사지게 형성하되, 상기 제2유입선(21)과 제2유출선(22) 사이에 하부로 곡면진 유체흐름면(23)을 형성하여 유체흐름면(23) 상부에 유체흐름공간(24)을 조성하며, 상기 제2유입선(21)과 제2유출선(22) 사이의 길이를 외측을 향할수록 점차 좁아지게 형성하되, 상기 제2유출선(22)과 인접된 유체흐름면(23)은 외측으로 향할수록 점진적으로 평평하게 형성한 유체흐름부(20)와; 상기 제1유입선(11)과 제2유입선(21)의 마주친 교차부위의 전방부를 절단한 제3유입선(31)을 성형하여, 유체저장부(10)에서 유체흐름부(20)로 유도되는 유체의 흐름에 제3유입선(31)을 통해 유체를 더 유입시키는 유체공급부(30)가 형성되는 것을 특징으로 한다.

    Abstract translation: 本发明涉及使用流体流动的推进装置，更具体地说，涉及使用流体流动的推进装置，其中在推进装置的上表面上产生的涡流被排放到外部，并且流体流过 添加的流体供应单元被增加以进一步提高涡流产生和排出的速度，从而改善装备有推进装置的产品的阻力和推力。 本发明的推进装置包括：流体存储单元（10），其具有形成在用于流体流入的前部第一入口管线（11）和后部第一出口管线（12）之间的向下弯曲的流体储存表面（13） 用于流体流出，形成在流体储存表面（13）的顶部上的流体存储空间（14）和形成在流体存储表面（13）的一侧的分隔壁（15）; 流体单元（20）具有形成在第一入口管线（11）的端部并沿向外和向后倾斜的第二入口管线（21），第二出口管线（22），其接触端部 ，并且在所述第一出口管线（12）中沿着向外和向后方向倾斜，形成在所述第二入口管线（21）和所述第二出口管线（22）之间的向下弯曲的流体流动表面（23）以及流体流动空间 （24），形成在流体流动表面（23）的顶部，第二入口管线（21）和第二出口管线（22）之间的长度随着向外流动而逐渐减小，流体流动表面（23） 第二出口线（22）向外延伸平坦化; 以及具有通过切割第一入口管线（11）和第二入口管线（21）之间的交叉部分的前部而形成的第三入口管线（31）的流体供应单元（30），以便通过第三入口 （31），流体从流体存储单元（10）引导到流体流动单元（20）的流体流动。

    INTEGRATED STARTING SYSTEM
    10.
    发明申请
    INTEGRATED STARTING SYSTEM 审中-公开
    集成起动系统

    公开(公告)号：WO1990006440A1

    公开(公告)日：1990-06-14

    申请号：PCT/US1989004484

    申请日：1989-10-10

    Applicant: SUNDSTRAND CORPORATION

    Inventor： SUNDSTRAND CORPORATION ,  RAAD, Bernard, H. ,  JOHNSEN, Tyrone, A.

    IPC: F02N11/08

    CPC classification number: F02N11/04 ,  B64D33/00

    Abstract: A starting system for an aircraft propulsion engine is disclosed. An electrical motor (62 or 122) is mounted within a case (14) in which first and second hydraulic units (102, 104) are operated as part of a constant speed drive transmission. The electric motor accelerates a motor-generator set (24) to a velocity near the synchronous speed. The motor-generator set is coupled to the drive shaft (20) by operation of the hydraulic units as a variable torque link. The electric motor functions both as a heat source of hydraulic fluid contained within the hydraulic pump and motor case during extreme low temperature conditions at which point the starting torque of the motor is initially insufficient to cause rotation of the output shaft and to further accelerate the motor-generator set up to a rotational velocity at which the motor-generator set may be operated synchronously at which the motor-generator set is coupled to the drive shaft (120) by operation of the hydraulic units as a variable torque link to rotate the engine. When the temperature of the hydraulic fluid within the case is below the stall temperature so that the electric motor has insufficient starting torque to initiate rotation, the heat generated by the windings heats the hydraulic oil to lower its viscosity to a point at which rotation may be initiated to permit the motor-generator set to be rapidly accelerated to operate as a synchronous motor during starting.

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