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公开(公告)号：US20180229851A1
公开(公告)日：2018-08-16
申请号：US15672448
申请日：2017-08-09
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
CPC classification number: B64D31/06 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2033/024 , F02C9/16 , G05D17/02 , Y02T50/62
Abstract: An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.
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公开(公告)号：US09903214B2
公开(公告)日：2018-02-27
申请号：US14721681
申请日：2015-05-26
Applicant: General Electric Company
Inventor： Ross Hartley Kenyon , Narendra Digamber Joshi
IPC: F01D5/34 , F01D5/18 , F04D29/58 , B23K26/34 , B22F3/105 , F04D29/32 , B23K26/342 , F04D29/02 , B23K103/18
CPC classification number: F01D5/34 , B22F3/1055 , B22F5/04 , B22F2301/15 , B23K26/342 , B23K2103/26 , B33Y10/00 , B33Y80/00 , C04B2235/6026 , C04B2235/665 , F01D5/02 , F01D5/087 , F01D5/18 , F01D5/282 , F01D5/284 , F04D29/023 , F04D29/321 , F04D29/324 , F04D29/584 , F05D2220/323 , F05D2230/22 , F05D2230/31 , F05D2240/30 , F05D2260/20 , F05D2300/175 , F05D2300/20 , F05D2300/603 , Y02P10/295 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A method of manufacturing an internally cooled blisk by additive manufacturing processes to provide weight reduction and power-to-weight ratio improvement, leading to improved efficiency, a decrease in fuel burn and lifecycle costs in an engine employing the internally cooled blisk. The method of manufacturing including defining a configuration for the internally cooled blisk, the configuration comprising a disk, an annular array of angularly spaced blades extending about a periphery of the disk and one or more internal cooling features defined within the internally cooled blisk. The method further including the step of programming the configuration into an additive manufacturing system. A powder is deposited into a chamber and an energy source is applied to the deposited powder to consolidate the powder into a cross-sectional shape corresponding to the defined configuration. Additionally provided is an internally cooled blisk.
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公开(公告)号：US20170146021A1
公开(公告)日：2017-05-25
申请号：US14950343
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
CPC classification number: F01D5/147 , B22F3/1055 , B22F5/04 , B22F7/06 , B22F2207/01 , B33Y10/00 , B33Y80/00 , F01D5/148 , F01D5/28 , F01D9/041 , F01D11/18 , F04D29/023 , F04D29/321 , F04D29/541 , F05D2220/32 , F05D2230/22 , F05D2230/31 , F05D2300/50212 , Y02P10/295
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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公开(公告)号：US20170009993A1
公开(公告)日：2017-01-12
申请号：US14791684
申请日：2015-07-06
Applicant: General Electric Company
Inventor： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
CPC classification number: F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
Abstract: A combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two annular trapped vortex cavities are located on the combustor liner and staged axially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities spaced apart from a radially outer wall and extending between an aft wall and a forward wall of each cavity. A plurality of injectors are configured tangentially relative to the circular radially outer wall to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid. A gas turbine engine including the combustor assembly is disclosed.
Abstract translation: 一种燃烧器组件，其包括在其中限定用于主流体的下游流动的燃烧室的燃烧器衬套。 至少两个环形的被捕获的涡流腔位于燃烧器衬套上并且沿轴向间隔分开。 空腔开口位于与径向外壁间隔开并在每个空腔的后壁和前壁之间延伸的至少两个环形捕获涡流腔中的每一个的径向内端。 多个喷射器相对于圆形径向外壁切向配置，以提供空气和燃料的喷射，以在相应的环形捕获的涡流空腔内形成燃料和空气混合物的环形旋转捕获涡流。 空腔开口处的燃料和空气混合物的环形旋转捕获的涡流基本上垂直于主流体的下游流动。 公开了一种包括燃烧器组件的燃气涡轮发动机。
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公开(公告)号：US09523537B2
公开(公告)日：2016-12-20
申请号：US13794205
申请日：2013-03-11
Applicant: General Electric Company
Inventor： James K. Prochaska , Narendra Digamber Joshi , Balachandar Naidu , Daniel Kaftori
IPC: F25D23/00 , F25D17/06 , F25B27/00 , F25B17/00 , F28C3/08 , F28B9/06 , F28C1/14 , F02C7/143 , F28F25/00 , F28B1/06
CPC classification number: F28C3/08 , F02C7/143 , F02C7/1435 , F28B1/06 , F28B9/06 , F28C1/14 , F28F25/00 , Y02T50/675
Abstract: A system includes an intercooler configured to receive an airflow from a first compressor, to transfer heat from the airflow to a working fluid, and to provide the airflow to a second compressor. The system also includes an evaporative chiller configured to receive the working fluid from the intercooler, to chill the working fluid via evaporative cooling within an ambient air environment, and to provide the working fluid to the intercooler. In addition, the system includes a desiccant system configured to reduce a humidity of ambient air within the evaporative chiller.
Abstract translation: 一种系统包括：中间冷却器，被配置为接收来自第一压缩机的气流，以将热量从气流传递到工作流体，并将气流提供给第二压缩机。 该系统还包括蒸发冷却器，其被配置为从中间冷却器接收工作流体，以通过在环境空气环境中的蒸发冷却来冷却工作流体，并将工作流体提供给中间冷却器。 另外，该系统包括配置成减少蒸发冷却器内的环境空气湿度的干燥剂系统。
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Patent Agency Ranking
126.发明申请AIR-SHIELDED FUEL INJECTION ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM 审中-公开空气燃料燃料注入装置，以帮助减少排放系统中的NOx排放公开(公告)号：US20160363319A1
公开(公告)日：2016-12-15
申请号：US14461069
申请日：2014-08-15
Applicant: General Electric Company
Inventor： Sarah Marie Monahan , Joel Meier Haynes , Narendra Digamber Joshi , David James Walker , Junwoo Lim , Krishna Kumar Venkatesan
CPC classification number: F23R3/286 , F02C7/222 , F05D2240/35 , F05D2240/36 , F23D14/64 , F23D2206/10 , F23D2900/11002
Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.
Abstract translation: 一种用于涡轮机组件的燃烧室中的空气屏蔽燃料喷射组件。 空气屏蔽燃料喷射组件通常包括包括多个燃料喷射端口的燃料歧管和包括多个空气喷射端口的空气歧管。 多个燃料喷射口中的每一个构造成将燃料柱引入混合器组件的环形腔中。 多个空气喷射端口中的每一个构造成围绕相关联的燃料喷射塔引入空气幕，以使燃料喷射塔的上游的再循环最小化并且增加燃料喷射塔到空腔中的穿透。 还公开了一种混合器组件和包括空气屏蔽燃料喷射组件的涡轮组件。
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公开(公告)号：US09500580B1
公开(公告)日：2016-11-22
申请号：US14730417
申请日：2015-06-04
Applicant: General Electric Company
Inventor： Chayan Mitra , Narendra Digamber Joshi , Vinayak Tilak , Gordon Raymond Smith , Eric YuHang Fung , Sandip Maity , Rachit Sharma , Steven Keith Handelsman
IPC: G01N21/3504 , G02B27/14 , G01N21/85
CPC classification number: G01N21/3504 , G01N21/85 , G01N33/0037 , G01N33/004 , G01N33/0054 , G01N2021/3129 , G01N2021/8578 , G02B27/141
Abstract: A gas detector and method are presented. The gas detector includes a launcher unit for coupling and merging light beams in mid-infrared and infrared wavelength ranges into a single light beam and directing the merged single light beam towards a gas flow path; a receiver unit for generating at least one photo detector current signal based on the light beam transmitted through the gas flow path; and a control unit for processing at least one photo detector current signal to measure concentration of the at least two gases present in the gas flow path.
Abstract translation: 提出了一种气体检测器和方法。 气体检测器包括用于将中红外和红外波长范围内的光束耦合并合并成单个光束并将合并的单个光束导向气体流动通道的发射单元; 接收器单元，用于基于透过气体流路的光束产生至少一个光电检测器电流信号; 以及控制单元，用于处理至少一个光电检测器电流信号，以测量气流路径中存在的至少两种气体的浓度。
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公开(公告)号：US20160319742A1
公开(公告)日：2016-11-03
申请号：US14489565
申请日：2014-09-18
Applicant: General Electric Company
Inventor： Roy James Primus , Adam Edgar Klingbeil , Narendra Digamber Joshi , Omowoleola Chukwuemeka Akinyemi , Thomas Michael Lavertu
CPC classification number: F02B63/04 , F01D15/10 , F02C3/10 , F02C3/13 , F02C6/00 , F02C6/08 , F02C6/12 , F02C6/20 , F02D41/0007 , F05D2220/40 , F05D2220/76 , Y02T10/144
Abstract: A system includes an engine coupled with a primary shaft that drives a first electric generator for generating electrical power via a gear subsystem, The system also includes a turbocharger assembly having at least one gas turbine engine configured for driving the primary shaft and coupled in parallel with the engine. The turbocharger assembly includes multiple compressors configured to provide a flow of compressed fluid into both the engine and the at least one gas turbine engine and multiple turbines configured to utilize exhausts from both the engine and the one gas turbine for driving the primary shaft. Further, the system includes a controller configured to operate a plurality of valves for controlling optimal intake fluid pressure into the engine and the turbocharger assembly and fuel injections into the engine and the at least one gas turbine engine.
Abstract translation: 一种系统包括与主轴联接的发动机，其驱动第一发电机以经由齿轮子系统产生电力。该系统还包括具有至少一个燃气涡轮发动机的涡轮增压器组件，该燃气涡轮发动机被配置为驱动主轴并与 引擎。 涡轮增压器组件包括多个压缩机，其配置成向发动机和至少一个燃气涡轮发动机提供压缩流体流，并且多个涡轮机被配置成利用来自发动机和一个燃气涡轮机的排气来驱动主轴。 此外，该系统包括控制器，该控制器被配置为操作多个阀，用于控制进入发动机和涡轮增压器组件的最佳进气流体压力以及向发动机和至少一个燃气涡轮发动机的燃料喷射。
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公开(公告)号：US20160163209A1
公开(公告)日：2016-06-09
申请号：US14560449
申请日：2014-12-04
Applicant: General Electric Company
Inventor： Zhi Zhou , Narendra Digamber Joshi , Rui Zhou , Hongwei Liao
CPC classification number: G08G5/065 , G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0078 , G08G5/0082
Abstract: A method implemented using at least one processor includes acquiring sensor data from a plurality sensors disposed on a vehicle configured to engage an aircraft for ground operation, wherein the aircraft is a member of a fleet of aircrafts. The method further includes receiving a plurality of environmental parameters from a supervisory system, wherein the supervisory system receives data from at least one of a gate, a service vehicle, a taxi vehicle, another aircraft, and a control center. The method also includes determining a plurality of contextual parameters representative of status of the vehicle based on the sensor data and the plurality of environmental parameters. The method further includes generating a plurality of control parameters based on the plurality of contextual parameters and the plurality of environmental parameters and providing at least one of the plurality of the control parameters to the vehicle for managing airport traffic.
Abstract translation: 使用至少一个处理器实现的方法包括从设置在车辆上的多个传感器获取传感器数据，所述多个传感器被配置成接合飞行器用于地面操作，其中所述飞行器是飞行器队列的成员。 该方法还包括从监控系统接收多个环境参数，其中监控系统从门，服务车辆，出租车车辆，其他飞行器和控制中心中的至少一个接收数据。 该方法还包括基于传感器数据和多个环境参数来确定表示车辆状态的多个语境参数。 该方法还包括基于多个上下文参数和多个环境参数生成多个控制参数，并将多个控制参数中的至少一个提供给车辆以管理机场交通。
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公开(公告)号：US20160159497A1
公开(公告)日：2016-06-09
申请号：US14560555
申请日：2014-12-04
Applicant: General Electric Company
Inventor： Zhi Zhou , Narendra Digamber Joshi , Rui Zhou , Hongwei Liao
CPC classification number: B64F1/227 , G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0078 , G08G5/0082 , G08G5/06 , G08G5/065 , Y02T50/826
Abstract: A method implemented using at least one of the processor includes disposing a power source on a vehicle, wherein the power source is configured to power auxiliary loads of the aircraft. The method also includes connecting a power source disposed on a vehicle configured to engage an aircraft for ground operation, to auxiliary loads of the aircraft via an on-board power system. The method also includes performing energy management of the aircraft during the period of ground operation. The method further includes disconnecting the power source when an alternate electrical power is available to the on-board power system.
Abstract translation: 使用处理器中的至少一个实现的方法包括在车辆上设置电源，其中电源被配置为对飞行器的辅助负载提供动力。 该方法还包括将布置在车辆上的配置成与飞机进行接地操作的电源相连接，经由车载电力系统连接飞行器的辅助负载。 该方法还包括在地面操作期间执行飞行器的能量管理。 该方法还包括当车载电力系统可用的替代电力时断开电源。
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