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    SYSTEM AND METHOD OF CONTROLLING COMBUSTOR DYNAMICS WITH A FUEL CELL
    4.
    发明公开
    SYSTEM AND METHOD OF CONTROLLING COMBUSTOR DYNAMICS WITH A FUEL CELL 审中-公开

    公开(公告)号：US20230187677A1

    公开(公告)日：2023-06-15

    申请号：US17550368

    申请日：2021-12-14

    Applicant: General Electric Company

    Inventor： Honggang Wang ,  Fei Han

    IPC: H01M8/2404

    CPC classification number: H01M8/2404 ,  B64D2041/005

    Abstract: A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: delivering the output products from the fuel cell to the combustion section to mitigate combustion dynamics within the combustion section.

    Inline fluid damper device
    5.
    发明授权
    Inline fluid damper device 有权

    公开(公告)号：US10808874B2

    公开(公告)日：2020-10-20

    申请号：US15827587

    申请日：2017-11-30

    Applicant: General Electric Company

    Inventor： Ramal Janith Samarasinghe ,  Nicholas Arthur Magina ,  Andrew Wickersham ,  Arin Cross ,  Fei Han

    IPC: F16L55/04 ,  F16L55/05 ,  F02M37/00 ,  F16L11/26 ,  F15D1/00

    Abstract: An inline fluid damper device comprises a flow-through conduit configured to be placed inside a larger exterior conduit through which a fluid flows. The flow-through conduit is elongated and extending around a center axis. The damper device also comprising an indirect flow conduit coupled with the flow-through conduit. The indirect flow conduit is also configured to be placed inside the larger exterior conduit. The flow-through conduit and the indirect flow conduit are configured to dampen one or more flow fluctuations or pressure fluctuations in the fluid flowing in the larger exterior conduit by dividing the fluid into a first portion that flows along the center axis through the flow-through conduit and a second portion that concurrently flows outside of the flow-through conduit along the center axis and along a different direction.

    Systems and methods for measuring temperature in a gas turbine using acoustic interference
    6.
    发明授权
    Systems and methods for measuring temperature in a gas turbine using acoustic interference 有权

    公开(公告)号：US10197456B2

    公开(公告)日：2019-02-05

    申请号：US15229613

    申请日：2016-08-05

    Applicant: General Electric Company

    Inventor： Eamon P. Gleeson ,  Fei Han

    IPC: G01K11/22 ,  G01K13/02 ,  G01M15/14

    Abstract: Systems and methods for measuring temperature in a gas turbine are disclosed. The method can include directing a first acoustic signal and a second acoustic signal towards a gas path in a turbine; receiving the first acoustic signal and the second acoustic signal at a downstream gas path location; combining the first acoustic signal and the second acoustic signal to create a combined acoustic signal, wherein the combined acoustic signal forms at least one of either a signal maxima or a signal minima; and based at least in part on the combined acoustic signal, determining a temperature of the gas path.

    Gas turbine assemblies and methods
    7.
    发明授权
    Gas turbine assemblies and methods 有权

    公开(公告)号：US11536457B2

    公开(公告)日：2022-12-27

    申请号：US17138048

    申请日：2020-12-30

    Applicant: General Electric Company

    Inventor： Owen Graham ,  Kwanwoo Kim ,  Nicholas Magina ,  Sharath Nagaraja ,  Fei Han

    IPC: F23R3/26 ,  F23R3/00 ,  F23R3/28 ,  F23R3/04 ,  F23R3/10 ,  F02C7/18 ,  F02C3/04

    Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.

    Gas turbine engine fuel manifold damper and method of dynamics attenuation
    8.
    发明授权
    Gas turbine engine fuel manifold damper and method of dynamics attenuation 有权

    公开(公告)号：US10415480B2

    公开(公告)日：2019-09-17

    申请号：US15486872

    申请日：2017-04-13

    Applicant: General Electric Company

    Inventor： Fei Han

    IPC: F02C7/22 ,  F23R3/28

    Abstract: The present disclosure is directed to a fuel manifold assembly for a gas turbine engine. The fuel manifold assembly defines a walled conduit through which a fuel flows in a fuel passage. The walled conduit defines a first end and a second end opposite of the first end along a length of the walled conduit. The fuel manifold assembly includes an exit manifold to which a fuel nozzle attaches. The fuel manifold assembly includes a damper assembly coupled to the walled conduit of the fuel manifold assembly. The damper assembly includes a walled tube extended from the walled conduit. The damper assembly further includes a walled enclosure defining a damper cavity therein. The damper cavity is in fluid communication with a damper passage defined within the walled tube, and the damper passage is in fluid communication with the fuel passage.

    Gas Turbine Engine Fuel Manifold Damper and Method of Dynamics Attenuation
    9.
    发明申请
    Gas Turbine Engine Fuel Manifold Damper and Method of Dynamics Attenuation 审中-公开

    公开(公告)号：US20180298825A1

    公开(公告)日：2018-10-18

    申请号：US15486872

    申请日：2017-04-13

    Applicant: General Electric Company

    Inventor： Fei Han

    IPC: F02C7/22 ,  F23R3/28

    CPC classification number: F02C7/222 ,  F05D2220/32 ,  F05D2260/96 ,  F23R3/28 ,  F23R2900/00013 ,  F23R2900/00014

    Abstract: The present disclosure is directed to a fuel manifold assembly for a gas turbine engine. The fuel manifold assembly defines a walled conduit through which a fuel flows in a fuel passage. The walled conduit defines a first end and a second end opposite of the first end along a length of the walled conduit. The fuel manifold assembly includes an exit manifold to which a fuel nozzle attaches. The fuel manifold assembly includes a damper assembly coupled to the walled conduit of the fuel manifold assembly. The damper assembly includes a walled tube extended from the walled conduit. The damper assembly further includes a walled enclosure defining a damper cavity therein. The damper cavity is in fluid communication with a damper passage defined within the walled tube, and the damper passage is in fluid communication with the fuel passage.

    Annular strip micro-mixers for turbomachine combustor
    10.
    发明授权
    Annular strip micro-mixers for turbomachine combustor 有权
    用于涡轮机燃烧器的环形微型混合器

    公开(公告)号：US09410704B2

    公开(公告)日：2016-08-09

    申请号：US13908156

    申请日：2013-06-03

    Applicant: General Electric Company

    Inventor： Qingguo Zhang ,  Fei Han

    IPC: F23R3/28 ,  F23N5/00

    CPC classification number: F23R3/286 ,  F23N5/003 ,  F23N2025/08 ,  F23N2041/20

    Abstract: A turbomachine combustor is provided. The turbomachine includes a combustion chamber and multiple micro-mixer nozzles arranged concentrically within a radial combustion liner and configured to receive fuel from one or more fuel supply pipes affixed to each of the plurality of micro-mixer nozzles at an upstream face. The multiple micro-mixer nozzle are also configured to receive air from a flow sleeve surrounding the radial combustion liner. Each of the micro-mixer nozzles include an annular strip having a multiple tubes or passages extending axially from the upstream face to a downstream face of each of the micro-mixer nozzles.

    Abstract translation: 提供涡轮机燃烧器。 涡轮机包括燃烧室和多个微型混合器喷嘴，其同心地布置在径向燃烧衬套内并且构造成在上游面处从固定到多个微混合器喷嘴中的每一个的一个或多个燃料供给管接收燃料。 多个微型混合器喷嘴还构造成从围绕径向燃烧衬套的流动套筒接收空气。 每个微型混合器喷嘴包括具有从每个微混合器喷嘴的上游面到下游面轴向延伸的多个管或多个管的环形条。

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