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    Gas turbine combustor
    81.
    发明授权
    Gas turbine combustor 有权

    公开(公告)号：US09765971B2

    公开(公告)日：2017-09-19

    申请号：US14539157

    申请日：2014-11-12

    申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.

    发明人： Yoshinori Matsubara ,  Keisuke Miura

    IPC分类号： F23R3/00 ,  F23R3/28 ,  F23R3/10 ,  F23D11/10 ,  F23R3/12 ,  F23C7/00

    CPC分类号： F23R3/28 ,  F23C7/002 ,  F23D11/107 ,  F23R3/10 ,  F23R3/12 ,  F23R3/286

    摘要： A gas turbine combustor having a burner including a plurality of fuel nozzles for injecting fuel, air hole plates positioned on a downstream side of the fuel nozzles and a plurality of air holes arranged in pairs with each of the fuel nozzles, and a combustion chamber for mixing fuel injected from the fuel nozzles and air injected from the air holes and injecting and burning the mixed fuel. Each of the fuel nozzles configuring the burners is provided with a projection in which a part of an outer edge of a section of the fuel nozzle is protruded outward; and the projection is arranged so as to be directed toward a center of the gas turbine combustor. The projection of the fuel nozzle is positioned on a downstream side of a flow of combustion air flowing around each of the fuel nozzles.

    COMBUSTOR BURNER ARRANGEMENT
    87.
    发明申请
    COMBUSTOR BURNER ARRANGEMENT 审中-公开
    COMBUSTOR燃烧器装置

    公开(公告)号：US20170045231A1

    公开(公告)日：2017-02-16

    申请号：US15305450

    申请日：2015-04-30

    申请人： Siemens Aktiengesellschaft

    发明人： Imogen Stevenson ,  Ronald Bickerton ,  Timothy Dolmansley

    IPC分类号： F23R3/38 ,  F23R3/12 ,  F02C7/264 ,  F23R3/28

    CPC分类号： F23R3/14 ,  F02C7/264 ,  F05D2220/32 ,  F23D11/12 ,  F23R3/04 ,  F23R3/12 ,  F23R3/286 ,  F23R3/38 ,  F23R2900/00004

    摘要： A fuel lance for a burner of a combustor has a fuel lance body defining a fuel flow passage and a liquid fuel tip attached thereto and in flow communication with fuel flow passage. The liquid fuel tip has a fuel outlet and an array of air passages having outlets which are arranged outside a blank sector of a circumference around the fuel outlet, the blank sector defined by an angle from 30° to 160°. A burner includes the fuel lance and the igniter and a main air flow passage to direct at least a part of a main air flow over the fuel lance and over the igniter, the blank sector has a centre-line angled between +120° and −120° from a radial line from the axis and passing through the fuel lance. A method includes rotating the fuel lance between a start-up condition and a second condition.

    摘要翻译： 用于燃烧器燃烧器的燃料喷枪具有燃料喷枪体，其限定燃料流动通道和附接到其上的液体燃料尖端并与燃料流动通道流动连通。 液体燃料尖端具有燃料出口和一排空气通道，其具有出口，该出口布置在围绕燃料出口的圆周的空白扇区的外侧，空白扇区由30°至160°的角度限定。 燃烧器包括燃料喷枪和点火器以及主空气流动通道，用于将主气流的至少一部分引导到燃料喷枪上方和点火器上方，空白扇区具有在+ 120°和+ 距离轴线的径向线120°，并穿过燃料喷枪。 一种方法包括在启动条件和第二状态之间旋转燃料喷枪。

    COMBUSTION CHAMBER COMPRISING ADDITIONAL INJECTION DEVICES OPENING UP DIRECTLY INTO CORNER RECIRCULATION ZONES, TURBOMACHINE COMPRISING SUCH A CHAMBER AND FUEL SUPPLY METHOD FOR SUCH A CHAMBER
    88.
    发明申请
    COMBUSTION CHAMBER COMPRISING ADDITIONAL INJECTION DEVICES OPENING UP DIRECTLY INTO CORNER RECIRCULATION ZONES, TURBOMACHINE COMPRISING SUCH A CHAMBER AND FUEL SUPPLY METHOD FOR SUCH A CHAMBER 审中-公开
    包括附加注射装置的燃烧室，其直接打开到角部再循环区域，包括这样的室的涡轮机和这样一个室的燃料供应方法

    公开(公告)号：US20170023251A1

    公开(公告)日：2017-01-26

    申请号：US15216029

    申请日：2016-07-21

    申请人： SNECMA

    发明人： Julien LEPAROUX ,  Joseph Burguburu

    IPC分类号： F23R3/34 ,  F02C9/28 ,  F23R3/28 ,  F23R3/00 ,  F23R3/14

    CPC分类号： F23R3/346 ,  F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/304 ,  F23R3/002 ,  F23R3/12 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R3/50 ,  F23R2900/03282

    摘要： A combustion chamber (18) for aircraft turbomachine, comprising an annular chamber end wall (40), an annular row of injection systems (42) mounted in the annular chamber end wall (40), each injection system comprising at least one air inlet swirler (56, 58) and a main fuel injection nozzle (54) configured to output a fuel stream centred on an injection axis (44) and comprising a central recirculation zone (62) and a corner recirculation zone (64) extending as an annulus around the central recirculation zone (62) chamber, and a plurality of additional fuel injection devices (70) mounted in the chamber end wall (40) and configured to inject fuel (71) directly into the corresponding corner recirculation zones (64) produced by the corresponding injection systems (42) at an operating speed less than or equal to the idling speed.

    摘要翻译： 一种用于飞机涡轮机的燃烧室（18），包括环形室端壁（40），安装在环形室端壁（40）中的环形排注射系统（42），每个喷射系统包括至少一个进气旋流器 （56,58）和主燃料喷射喷嘴（54），其被配置为输出以喷射轴线（44）为中心的燃料流，并且包括中心再循环区域（62）和作为环形区域延伸的角落再循环区域（64） 中心再循环区（62）腔室和多个附加的燃料喷射装置（70），其安装在腔室端壁（40）中，并被配置为将燃料（71）直接喷射到由 相应的注射系统（42）以小于或等于怠速的操作速度。

    BURNER ARRANGEMENT INCLUDING AN AIR SUPPLY WITH TWO FLOW PASSAGES
    90.
    发明申请
    BURNER ARRANGEMENT INCLUDING AN AIR SUPPLY WITH TWO FLOW PASSAGES 有权
    燃烧器布置包括两个流量通道的空气供应

    公开(公告)号：US20160298844A9

    公开(公告)日：2016-10-13

    申请号：US13936424

    申请日：2013-07-08

    申请人： ALSTOM Technology Ltd

    发明人： Stefano BERNERO ,  Ennio PASQUALOTTO ,  Ewald FREITAG

    IPC分类号： F23R3/14 ,  F23R3/28

    CPC分类号： F23R3/14 ,  F23R3/12 ,  F23R3/28 ,  F23R3/54 ,  F23R2900/03043

    摘要： The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.

    摘要翻译： 本发明涉及用于生产在燃气轮机中膨胀的热气体的燃烧器装置，包括在集气室内的燃烧器，其中燃烧器具有用于燃料喷射的装置，用于供气的装置和用于在其内部产生可燃燃料/空气混合物的装置 燃烧器和下游的燃烧室，所述燃烧器具有流体连接到燃气轮机的出口。 本发明的特征在于，用于供气的装置包括至少两个分离的流动通道，并且两个流动通道中的一个被第一供给压力供给，而另一个流动通道被供给第二供给压力。