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    COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING
    71.
    发明申请
    COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING 审中-公开
    用于燃气涡轮发动机的燃烧器组件和组装方法

    公开(公告)号：US20170016620A1

    公开(公告)日：2017-01-19

    申请号：US14801962

    申请日：2015-07-17

    Applicant: General Electric Company

    Inventor： Matthieu Marc Masquelet ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Sarah Marie Monahan

    IPC: F23R3/00 ,  F23R3/28

    Abstract: A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.

    Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括圆顶组件，联接到圆顶组件的燃料喷嘴和整流罩组件。 整流罩组件包括联接到圆顶组件的径向内部整流罩，以及包括第一整流罩构件和每个围绕燃料喷嘴定位的第二整流罩构件的径向外罩。 第一和第二整流罩构件基本上对准以限定基本上连续的流动路径，其构造成引导围绕圆顶组件的空气流。

    TURBINE ENGINE ASSEMBLY AND METHOD OF MANUFACTURING
    73.
    发明申请
    TURBINE ENGINE ASSEMBLY AND METHOD OF MANUFACTURING 审中-公开
    涡轮发动机总成及制造方法

    公开(公告)号：US20160160647A1

    公开(公告)日：2016-06-09

    申请号：US14802074

    申请日：2015-07-17

    Applicant: General Electric Company

    Inventor： Douglas Carl Hofer ,  Narendra Digamber Joshi ,  Michael Solomon Idelchik

    IPC: F01D1/04

    CPC classification number: F01D1/04 ,  F02K3/065 ,  F02K3/077

    Abstract: A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed.

    Abstract translation: 提供涡轮发动机组件。 该组件包括低压涡轮机组件，该低压涡轮机组件包括构造成以第一旋转速度沿第一旋转方向旋转的第一涡轮部分和构造成以第二旋转速度沿第二旋转方向旋转的第二涡轮机部分。 第二旋转方向与第一旋转方向相反，第二旋转速度低于第一旋转速度。 组件还包括联接到第一涡轮部分的第一驱动轴和风扇组件，其包括联接到第一驱动轴的第一风扇部分，使得第一风扇部分以第一旋转速度沿第一旋转方向旋转，并且 第二风扇部分联接到第二涡轮机部分，使得第二风扇部分在第二旋转方向上以第二转速旋转。

    CORRUGATED CYCLONE MIXER ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS AND IMPROVE OPERABILITY IN A COMBUSTOR SYSTEM
    74.
    发明申请
    CORRUGATED CYCLONE MIXER ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS AND IMPROVE OPERABILITY IN A COMBUSTOR SYSTEM 审中-公开
    腐蚀性气旋混合器组装，以减少NOx排放并提高COMBUSTOR系统的可操作性

    公开(公告)号：US20160061452A1

    公开(公告)日：2016-03-03

    申请号：US14469029

    申请日：2014-08-26

    Applicant: General Electric Company

    Inventor： David James Walker ,  Joel Meier Haynes ,  Narendra Digamber Joshi ,  Junwoo Lim ,  Krishna Kumar Venkatesan ,  Sarah Marie Monahan

    IPC: F23R3/28

    Abstract: A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer.

    Abstract translation: 一种用于涡轮发动机的燃料喷射组件的波纹旋风混合器。 波纹旋风混合器通常包括环形壳体，其包括凸缘部分和配置在凸缘部分下游的唇部。 混合器还包括设置在其中的旋流器，用于在波纹旋风混合器中引起气旋运动。 旋流器构造在凸缘部分的上游并且包括多个旋流器叶片以产生旋转空气流。 所述唇部形成在所述旋流器下游的出口并且在后端处包括多个波纹。 多个波纹被配置成将旋转空气流和流经波纹旋风混合器的喷射燃料流混合。 另外公开了一种燃料喷射组件和包括波纹旋风混合器的涡轮组件。

    FUEL INJECTOR TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM
    75.
    发明申请
    FUEL INJECTOR TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM 审中-公开
    燃油喷射器，以减少燃烧系统中的NOx排放

    公开(公告)号：US20160033132A1

    公开(公告)日：2016-02-04

    申请号：US14447967

    申请日：2014-07-31

    Applicant: General Electric Company

    Inventor： Krishna Kumar Venkatesan ,  Joel Meier Haynes ,  Narendra Digamber Joshi ,  David James Walker ,  Junwoo Lim ,  Sarah Marie Monahan

    IPC: F23R3/28 ,  F23R3/10 ,  F02C7/22 ,  F23R3/42

    CPC classification number: F23R3/286 ,  F23R3/10 ,  F23R3/34 ,  F23R3/42

    Abstract: A fuel injector to reduce NOx emissions in a combustor system. The fuel injector including a housing, at least one oxidizer flow path, extending axially through the fuel injector housing and defining therein one or more oxidizer flow paths for an oxidizer stream and a fuel manifold, extending axially through the fuel injector housing and defining therein one or more fuel flow path. The fuel manifold includes a forward portion and an aft portion including an aft face. A plurality of fuel injector outlets are defined in the aft portion, wherein the plurality of fuel injector outlets are configured to inject a fuel flow along a mid-plane of the fuel injector and away from a downstream wall. The fuel flow exiting the fuel manifold undergoes circumferential and radial mixing upon interaction with the oxidizer stream. Additionally disclosed is a combustor system including the fuel injector.

    Abstract translation: 一种用于减少燃烧器系统中的NOx排放的燃料喷射器。 燃料喷射器包括壳体，至少一个氧化剂流动路径，其轴向延伸穿过燃料喷射器壳体并且在其中限定用于氧化剂流和燃料歧管的一个或多个氧化剂流动路径，轴向延伸穿过燃料喷射器壳体并在其中限定一个 或更多的燃料流动路径。 燃料歧管包括前部和后部，其包括后表面。 多个燃料喷射器出口限定在后部部分中，其中多个燃料喷射器出口构造成沿着燃料喷射器的中间面喷射燃料流并远离下游壁。 离开燃料歧管的燃料流在与氧化剂流相互作用时经历周向和径向混合。 另外公开了一种包括燃料喷射器的燃烧器系统。

    DESICCANT BASED CHILLING SYSTEM
    76.
    发明申请
    DESICCANT BASED CHILLING SYSTEM 有权
    基于冷却系统

    公开(公告)号：US20140250935A1

    公开(公告)日：2014-09-11

    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: F28C3/08

    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。

    Systems and methods for removing heat from aircraft components
    78.
    发明授权
    Systems and methods for removing heat from aircraft components 有权

    公开(公告)号：US11753178B2

    公开(公告)日：2023-09-12

    申请号：US16681292

    申请日：2019-11-12

    Applicant: General Electric Company

    Inventor： Lawrence Bernard Kool ,  Narendra Digamber Joshi

    IPC: B64D37/34 ,  B64C1/38 ,  B64D33/08 ,  F02C7/224

    CPC classification number: B64D37/34 ,  B64C1/38 ,  B64D33/08 ,  F02C7/224

    Abstract: A system for removing heat from an aircraft component includes: a heat exchanger in proximity to an aircraft component and having an inlet, an outlet, and an internal surface coated with a catalyst; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system. A method of removing heat from an aircraft component includes providing a heat exchanger in proximity to an aircraft component, the heat exchanger being in fluid communication with a source of hydrocarbon fuel and a source of water and having an internal surface coated with a catalyst; introducing a hydrocarbon fuel into the heat exchanger; introducing oxygen into the heat exchanger; contacting the hydrocarbon fuel with the catalyst; and cracking the hydrocarbon fuel.

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