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    COMBUSTOR STRUCTURE
    3.
    发明申请
    COMBUSTOR STRUCTURE 审中-公开
    COMBUSTOR结构

    公开(公告)号：US20100005804A1

    公开(公告)日：2010-01-14

    申请号：US12171386

    申请日：2008-07-11

    申请人： Wei Chen ,  David Martin Johnson ,  Ronald James Chila ,  Joseph Citeno

    发明人： Wei Chen ,  David Martin Johnson ,  Ronald James Chila ,  Joseph Citeno

    IPC分类号： F02C1/00

    CPC分类号： F23R3/16 ,  F01D9/023 ,  F23R3/002 ,  F23R2900/00014 ,  F23R2900/03044

    摘要： A combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward a turbine. At least one combustor sleeve is located outside of the combustion chamber and is capable of reducing a magnitude of acoustic waves in the combustion chamber. The at least one combustor liner and the at least one combustor sleeve define at least one flow channel therebetween. Further, a combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward turbomachinery. At least one combustor sleeve disposed outside of the combustion chamber and is capable of controlling distribution of fluid flow in the combustor to modify a uniformity of the fluid flow to the combustion chamber.

    摘要翻译： 燃烧器包括限定燃烧室的至少一个燃烧器衬套，其能够将燃烧产物引向涡轮。 至少一个燃烧器套筒位于燃烧室的外部，并且能够减小燃烧室中的声波的大小。 所述至少一个燃烧器衬套和所述至少一个燃烧器套筒在其间限定至少一个流动通道。 此外，燃烧器包括限定能够将燃烧产物引导到涡轮机械的燃烧室的至少一个燃烧器衬套。 至少一个燃烧器套筒设置在燃烧室的外部，并且能够控制燃烧器中的流体流动的分布，以改变流向燃烧室的流体的均匀性。

    Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
    4.
    发明申请
    Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine 审中-公开
    具有径向分段流动通道的燃气轮机预混合器和用于在燃气轮机中混合空气和气体的方法

    公开(公告)号：US20090056336A1

    公开(公告)日：2009-03-05

    申请号：US11892891

    申请日：2007-08-28

    申请人： Ronald James Chila ,  John Charles Intile ,  Joseph Citeno ,  Mert E. Berkman

    发明人： Ronald James Chila ,  John Charles Intile ,  Joseph Citeno ,  Mert E. Berkman

    IPC分类号： F02C1/00

    CPC分类号： F23R3/286 ,  F23C2900/07001 ,  F23D2900/14004 ,  F23R3/14

    摘要： A burner for use in a combustion system of an industrial gas turbine. The burner includes a fuel/air premixer including a splitter vane defining a first, radially inner passage and a second, radially outer passage, the first and second passages each having air flow turning vane portions which impart swirl to the combustion air passing through the premixer. The vane portions in each passage are commonly configured to impart a same swirl direction in each passage. A plurality of splitter vanes may be provided to define three or more annular passages in the premixer.

    摘要翻译： 一种用于工业燃气轮机燃烧系统的燃烧器。 燃烧器包括燃料/空气预混合器，其包括限定第一径向内部通道的分流叶片和第二径向外部通道，所述第一和第二通道各自具有气流转动叶片部分，其向通过预混合器的燃烧空气施加漩涡 。 每个通道中的叶片部分通常构造成在每个通道中赋予相同的旋转方向。 可以设置多个分流叶片以在预混合器中限定三个或更多个环形通道。

    Methods and Systems for Controlling a Combustor in Turbine Engines
    5.
    发明申请
    Methods and Systems for Controlling a Combustor in Turbine Engines 有权
    用于控制涡轮发动机燃烧器的方法和系统

    公开(公告)号：US20100162724A1

    公开(公告)日：2010-07-01

    申请号：US12347147

    申请日：2008-12-31

    申请人： Geoffrey David Myers ,  Lewis Berkley Davis, JR. ,  Timothy Andrew Healy ,  Joseph Citeno

    发明人： Geoffrey David Myers ,  Lewis Berkley Davis, JR. ,  Timothy Andrew Healy ,  Joseph Citeno

    IPC分类号： F02C9/00

    CPC分类号： F23R3/26 ,  F23N5/00 ,  F23N2041/20 ,  F23R2900/00013

    摘要： Embodiments of methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

    摘要翻译： 提供了用于控制燃气涡轮发动机的燃烧器的方法和系统的实施例。 根据一个示例性实施例，系统包括与用于燃气涡轮发动机的燃烧器的至少一个空气路径相关联的空气控制组件。 另外，该系统还包括用于感测燃气涡轮发动机的至少一个操作参数的至少一个传感器。 此外，该系统还包括可操作以接收由至少一个传感器感测的至少一个操作参数的控制器，并且还可操作以至少部分地基于由所述至少一个传感器感测的至少一个操作参数来选择性地控制空气控制组件 至少一个传感器。

    COMBUSTOR PORTION FOR A TURBOMACHINE AND METHOD OF OPERATING A TURBOMACHINE
    6.
    发明申请
    COMBUSTOR PORTION FOR A TURBOMACHINE AND METHOD OF OPERATING A TURBOMACHINE 有权
    涡轮机的燃烧器部件和操作涡轮机的方法

    公开(公告)号：US20130025289A1

    公开(公告)日：2013-01-31

    申请号：US13193865

    申请日：2011-07-29

    申请人： Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

    发明人： Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

    IPC分类号： F02C7/22

    CPC分类号： F23R3/286 ,  F23R3/343 ,  F23R3/346

    摘要： A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.

    摘要翻译： 涡轮机燃烧器部分包括燃烧室。 中心喷嘴设置在燃烧室内，并包括中心喷嘴入口和中心喷嘴出口。 外部预混合喷嘴位于中心喷嘴的径向外侧，并且包括布置在中心喷嘴出口上游的外喷嘴入口和外喷嘴出口。 后期的稀薄喷射器位于中心喷嘴和外部预混喷嘴的下游。 燃烧器部分包括布置在外部喷嘴出口下游的第一燃烧区域，布置在中心喷嘴出口下游的第二燃烧区域和布置在中心喷嘴出口下游的第三燃烧区域。 选择性地操作中心注射喷嘴，外部预混合喷嘴和后部稀薄喷射器，以在第一，第二和第三燃烧区域中建立燃烧火焰前沿。

    Aspirating pyrometer with platinum thermocouple and radiation shields
    7.
    发明授权
    Aspirating pyrometer with platinum thermocouple and radiation shields 失效
    吸气高温计用铂热电偶和辐射屏蔽

    公开(公告)号：US5348395A

    公开(公告)日：1994-09-20

    申请号：US987964

    申请日：1992-12-11

    申请人： Robert A. Corr, II ,  Joseph Citeno

    发明人： Robert A. Corr, II ,  Joseph Citeno

    IPC分类号： G01K1/08 ,  G01K1/12 ,  G01K13/02

    CPC分类号： G01K1/12 ,  G01K1/08 ,  G01K13/022

    摘要： An aspirating or suction pyrometer for measuring hot combustion gases. A thermocouple in the pyrometer has a temperature sensitive junction formed of platinum alloys. The thermocouple junction is insulated and is encased within a platinum alloy sheath. The sheathed thermocouple is mounted within inner and outer tubular radiation shields. These shields are formed of a platinum alloy having a radiation emissivity substantially the same as the thermocouple. The shields block radiated heat from the flame and combustion chamber from being transferred to the thermocouple. The radiation shields do not themselves radiate heat to the thermocouple because the shields and thermocouple are at the same temperature and formed of substantially the same noble alloys.

    摘要翻译： 用于测量热燃气的吸气或吸气高温计。 高温计中的热电偶具有由铂合金形成的温度敏感结。 热电偶接头是绝缘的，并被封装在铂合金护套内。 护套热电偶安装在内部和外部管状辐射屏蔽内。 这些屏蔽由具有与热电偶基本相同的辐射辐射率的铂合金形成。 屏蔽块将来自火焰和燃烧室的辐射热量传递到热电偶。 辐射屏蔽本身不会向热电偶辐射热量，因为屏蔽和热电偶处于相同的温度并由大体上相同的贵金属合金形成。

    Methods and systems for operating gas turbine engines
    9.
    发明授权
    Methods and systems for operating gas turbine engines 有权
    运行燃气涡轮发动机的方法和系统

    公开(公告)号：US08122725B2

    公开(公告)日：2012-02-28

    申请号：US11933898

    申请日：2007-11-01

    申请人： Geoffrey David Myers ,  David August Snider ,  Eric Motter ,  Daniel R. Tegel ,  James Harper ,  Stephen R. Watts ,  Joseph Citeno

    发明人： Geoffrey David Myers ,  David August Snider ,  Eric Motter ,  Daniel R. Tegel ,  James Harper ,  Stephen R. Watts ,  Joseph Citeno

    IPC分类号： F02C7/22 ,  F02C9/26 ,  F02C9/00 ,  F02C3/00

    CPC分类号： F02C7/228

    摘要： Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

    摘要翻译： 提供了用于在燃气涡轮发动机中输送燃料的方法和系统。 该系统包括多个罐式环形燃烧器，其包括多个罐环形燃烧器中的至少第一组燃烧器和多个罐形环形燃烧器的至少第二组燃烧器，其中每组燃烧器由单独的 可控的燃油输送系统。 该方法包括以第一燃料排程向第一组燃料供应燃料，并在第一燃料运行方式中将第二燃料的燃料供应给第二组燃料，其中第二燃料计划与第一燃料计划不同，以及 在第二工作模式期间将第二燃料计划的燃料供应到第一和第二组燃烧器。