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11.发明授权公开(公告)号：US10288291B2
公开(公告)日：2019-05-14
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
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.
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公开(公告)号：US10202206B2
公开(公告)日：2019-02-12
申请号：US14560555
申请日：2014-12-04
Applicant: General Electric Company
Inventor： Zhi Zhou , Narendra Digamber Joshi , Rui Zhou , Hongwei Liao
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.
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公开(公告)号：US10196898B2
公开(公告)日：2019-02-05
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
IPC: F01D5/14 , F01D5/28 , F01D9/04 , F01D11/18 , B33Y10/00 , B33Y80/00 , B22F3/105 , B22F7/06 , B22F5/04 , F04D29/02 , F04D29/32 , F04D29/54
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：US09803552B2
公开(公告)日：2017-10-31
申请号：US14927578
申请日：2015-10-30
Applicant: General Electric Company
Inventor： Yuxin Zhang , Obulesu Chatakonda , Soumya Gudiyella , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet , Shashank Yellapantula
CPC classification number: F02C7/222 , F02C7/04 , F23R3/28 , F23R3/286 , F23R2900/00004
Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.
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公开(公告)号：US09732670B2
公开(公告)日：2017-08-15
申请号：US14103928
申请日：2013-12-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
Abstract: A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.
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Patent Agency Ranking
公开(公告)号：US20170184020A1
公开(公告)日：2017-06-29
申请号：US14982793
申请日：2015-12-29
Applicant: General Electric Company
Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.
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公开(公告)号：US20170122211A1
公开(公告)日：2017-05-04
申请号：US14927578
申请日：2015-10-30
Applicant: General Electric Company
Inventor： Yuxin Zhang , Obulesu Chatakonda , Soumya Gudiyella , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet , Shashank Yellapantula
CPC classification number: F02C7/222 , F02C7/04 , F23R3/28 , F23R3/286 , F23R2900/00004
Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.
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公开(公告)号：US09534788B2
公开(公告)日：2017-01-03
申请号：US14243951
申请日：2014-04-03
Applicant: General Electric Company
Inventor： Suhui Li , Narendra Digamber Joshi , Keith Robert McManus
Abstract: A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct an outer annular swirler located adjacent an upstream end of the mixing duct for swirling air flowing therethrough in a first swirl direction and an inner annular swirler located adjacent of the mixing duct upstream end for swirling air flowing therethrough in a second swirl direction. The system includes a hub separating the inner and outer annular swirlers to permit independent rotation of an air stream therethrough and multiple hollow paths located radially outward around the centerbody fuel injector and at a radially inward side of the inner annular swirler for allowing a flow of sweeping air over the surface of the centerbody fuel injector.
Abstract translation: 用于在燃气涡轮发动机中燃烧之前预混合燃料和空气的系统包括混合管道，沿着混合管道的中心轴线定位的中心体燃料喷射器，位于混合管道的上游端附近的外部环形旋流器，用于旋转空气流动 在第一旋转方向穿过并且位于邻近混合管道上游端的内部环形旋流器，用于在第二旋转方向上流过其中的涡流。 该系统包括分隔内环形旋流器和外环形旋流器的毂，以允许空气流独立旋转，以及位于中心体燃料喷射器周围径向向外的多个中空路径，以及内环形旋流器的径向内侧， 空心在中心体燃油喷射器的表面上。
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19.发明申请PITCH CHANGE MECHANISM FOR SHROUDED FAN WITH LOW FAN PRESSURE RATIO 有权用于风扇压力比低的风扇的变更机构（PITCH CHANGE FOR SHROUDED FAN LOW FAN PRESSURE RATIO）公开(公告)号：US20160363050A1
公开(公告)日：2016-12-15
申请号：US14735260
申请日：2015-06-10
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
CPC classification number: F01D7/00 , F01D15/10 , F02K1/66 , F02K3/06 , F02K3/075 , F05D2220/32 , F05D2220/327 , F05D2220/36 , F05D2220/768 , F05D2240/51 , F05D2260/74 , Y02T50/672
Abstract: A shrouded fan assembly for use with a gas turbine engine includes a central hub and a plurality of variable-pitch fan blades coupled to and extending radially outward from the central hub. Each variable-pitch fan blade includes a radially outer tip is rotatable about a longitudinal axis extending therethrough. A shroud is coupled to each radially outer tip.
Abstract translation: 与燃气涡轮发动机一起使用的带罩的风扇组件包括中心毂和多个可变间距风扇叶片，其联接到中心毂的径向向外并从其延伸。 每个可变间距风扇叶片包括径向外部末端可围绕其延伸穿过的纵向轴线旋转。 护罩耦合到每个径向外部末端。
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公开(公告)号：US20160163208A1
公开(公告)日：2016-06-09
申请号：US14560311
申请日：2014-12-04
Applicant: General Electric Company
Inventor： Zhi Zhou , Narendra Digamber Joshi , Rui Zhou , Craig Hoover
CPC classification number: G06K9/00805 , B64F1/228 , G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0082 , G08G5/045 , G08G5/065 , Y02T50/826
Abstract: A method implemented using at least one processor includes receiving a plurality of images acquired from a plurality of image sensors disposed on a vehicle configured to engage an aircraft for ground operations. The method further includes determining at least one parameter about a potential obstacle based on the plurality of images and a machine vision algorithm. The method also includes generating an alert signal based on the at least one parameter, useful for avoiding collision of the aircraft.
Abstract translation: 使用至少一个处理器实现的方法包括接收从设置在车辆上的多个图像传感器获取的多个图像，所述多个图像传感器被配置为接合飞机用于地面操作。 该方法还包括基于多个图像和机器视觉算法确定关于潜在障碍物的至少一个参数。 该方法还包括基于至少一个参数产生警报信号，其有助于避免飞行器的碰撞。
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