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    Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
    3.
    发明授权
    Co-swirl orientation of combustor effusion passages for gas turbine engine combustor 有权

    公开(公告)号：US10317080B2

    公开(公告)日：2019-06-11

    申请号：US15037484

    申请日：2014-12-03

    Applicant: United Technologies Corporation

    Inventor： John S. Tu, Jr. ,  Timothy S. Snyder ,  James B. Hoke ,  James P. Bangerter ,  Dennis J. Duhamel ,  David A. Burns

    IPC: F23R3/00 ,  F23R3/06

    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

    MODIFIED FLOATWALL PANEL DILUTION HOLE COOLING
    6.
    发明申请
    MODIFIED FLOATWALL PANEL DILUTION HOLE COOLING 审中-公开
    改装浮板面板冷却孔冷却

    公开(公告)号：US20160265777A1

    公开(公告)日：2016-09-15

    申请号：US14884506

    申请日：2015-10-15

    Applicant: United Technologies Corporation

    Inventor： James B. Hoke ,  David Kwoka

    IPC: F23R3/06 ,  F23R3/60 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/03041 ,  Y02T50/675

    Abstract: Aspects of the disclosure are directed to a liner of an aircraft. The liner comprises a panel including at least one dilution hole, a rail coupled to the panel, and at least one effusion cooling hole located between a wall of the at least one dilution hole and a side of the rail. The liner may be associated with a combustion engine of the aircraft.

    Abstract translation: 本公开的方面针对飞机的班轮。 该衬垫包括一个面板，该面板包括至少一个稀释孔，连接到该面板的导轨以及位于该至少一个稀释孔的壁与该轨道的一侧之间的至少一个积液冷却孔。 衬套可以与飞行器的内燃机相关联。

    FUEL SYSTEM FOR TONE CONTROL AND OPERABILITY
    7.
    发明申请
    FUEL SYSTEM FOR TONE CONTROL AND OPERABILITY 有权
    燃油系统用于音调控制和操作

    公开(公告)号：US20160195024A1

    公开(公告)日：2016-07-07

    申请号：US14884487

    申请日：2015-10-15

    Applicant: United Technologies Corporation

    Inventor： James B. Hoke ,  Anthony Van

    IPC: F02C9/26

    CPC classification number: F02C9/263 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2260/96 ,  F05D2270/14

    Abstract: Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated with the at least one aircraft engine, causing a valve coupled to a fuel supply and each of the nozzles to open when it is determined that the state of operation indicates a high power state relative to at least one threshold, and causing the valve to close when it is determined that the state of operation indicates a low power state relative to the at least one threshold.

    Abstract translation: 本公开的方面旨在通过以下方式来控制燃料到与至少一个飞机发动机相关联的多个喷嘴的分配：确定与至少一个飞机发动机相关联的操作状态，导致与燃料供应连接的阀和每个 当确定操作状态相对于至少一个阈值指示高功率状态时，并且当确定操作状态指示相对于at处于低功率状态时使阀闭合 至少一个门槛。

    FUEL DISTRIBUTION WITHIN A GAS TURBINE ENGINE COMBUSTOR
    8.
    发明申请
    FUEL DISTRIBUTION WITHIN A GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃油涡轮发动机燃油分配

    公开(公告)号：US20130199200A1

    公开(公告)日：2013-08-08

    申请号：US13832507

    申请日：2013-03-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James B. Hoke ,  Timothy S. Snyder ,  David Kwoka ,  Robert M. Sonntag

    IPC: F02C7/22

    CPC classification number: F02C7/222 ,  F02C7/22 ,  F02C7/228 ,  F02C9/28

    Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

    Abstract translation: 用于燃气涡轮发动机的燃料系统包括布置在上死点的每一侧上的多个双面喷嘴和多个单面喷嘴。 主歧管可操作以将燃料传送到多个双相喷嘴中的每一个中的主流喷射器，并且次级歧管可操作以将燃料传送到多个双相喷嘴中的每一个中的二次流喷射，并且每个二次喷嘴中的次流喷射 的多个单体喷嘴。 与主歧管和次级歧管连通的均衡阀将不同压力的燃料分配到主歧管和次级歧管。

    Gas Turbine Combustor
    9.
    发明申请
    Gas Turbine Combustor 有权
    燃气轮机燃烧器

    公开(公告)号：US20130186099A1

    公开(公告)日：2013-07-25

    申请号：US13761454

    申请日：2013-02-07

    Applicant: United Technologies Corporation

    Inventor： James B. Hoke

    IPC: F23R3/14 ,  F23R3/34

    CPC classification number: F23R3/14 ,  F23R3/06 ,  F23R3/343 ,  F23R3/50 ,  Y02T50/675

    Abstract: A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.

    Abstract translation: 用于具有环形燃烧室的燃气涡轮发动机的燃烧器包括多个主燃料喷射和空气旋流器组件和多个引燃燃料喷射和空气旋流器组件，其设置在围绕前舱壁的周向延伸部延伸的周向环中。 多个先导燃料喷射和空气旋流器组件散布在主燃料喷射和空气旋流器组件的周向环中并且布置在其中。 响应于燃气涡轮发动机的功率需求水平，被供应到燃烧器的燃料被选择性地分布在多个主燃料喷射和空气旋流器组件和多个先导燃料喷射和空气旋流器组件之间。

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