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    COMBUSTOR LINER
    1.
    发明申请
    COMBUSTOR LINER 审中-公开

    公开(公告)号：US20190264923A1

    公开(公告)日：2019-08-29

    申请号：US16407821

    申请日：2019-05-09

    Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

    Inventor： Masayoshi KOBAYASHI ,  Takeo ODA ,  Takeo NISHIURA ,  Tomoko TSURU ,  Takaya HAMAMOTO ,  Takeshi TAKAGI ,  Osamu HISAMATSU ,  Hirotaka KURASHIMA

    IPC: F23R3/60 ,  F23R3/00 ,  F23R3/10

    Abstract: A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

    FUEL INJECTOR
    2.
    发明申请
    FUEL INJECTOR 有权
    喷油器

    公开(公告)号：US20130327849A1

    公开(公告)日：2013-12-12

    申请号：US13908578

    申请日：2013-06-03

    Applicant: JAPAN AEROSPACE EXPLORATION AGENCY ,  KAWASAKI JUKOGYO KABUSHIKI KAISHA

    Inventor： Ryusuke MATSUYAMA ,  Masayoshi KOBAYASHI ,  Atsushi HORIKAWA ,  Hitoshi FUJIWARA

    IPC: F02M23/12

    CPC classification number: F02M23/12 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  Y02T10/146

    Abstract: A fuel injector includes a pilot fuel injector, configured to inject the fuel into a combustion chamber, and a main fuel injector provided coaxially with the pilot fuel injector so as to surround the pilot fuel injector and configured to have a main flow path to generate a premixed air-fuel mixture. The main flow path includes an outer main air passage located radially outwardly and configured to supply a compressed air in an axial direction into an annular premixed air-fuel mixture passage, an inner main air passage located radially inwardly and configured to supply the compressed air into the premixed air-fuel mixture passage from a radially inner side. The injector further includes a main fuel injection port to inject the fuel from an axially upstream side into the inner main air passage.

    Abstract translation: 燃料喷射器包括引燃燃料喷射器，其被配置为将燃料喷射到燃烧室中;以及主燃料喷射器，其与引燃燃料喷射器同轴地设置，以围绕引燃燃料喷射器并且构造成具有主流路以产生 预混合空气燃料混合物。 主流路包括径向向外设置的外部主空气通道，其构造成沿轴向将压缩空气供应到环形预混合空气 - 燃料混合物通道中，径向向内设置的内部主空气通道，并且构造成将压缩空气供应到 预混合空气燃料混合物通道从径向内侧。 喷射器还包括用于将燃料从轴向上游侧喷射到内部主空气通道中的主燃料喷射口。

    GAS TURBINE COMBUSTOR
    5.
    发明申请
    GAS TURBINE COMBUSTOR 有权
    气体涡轮搅拌机

    公开(公告)号：US20140083105A1

    公开(公告)日：2014-03-27

    申请号：US14091619

    申请日：2013-11-27

    Applicant: Japan Aerospace Exploration Agency ,  Kawasaki Jukogyo Kabushiki Kaisha

    Inventor： Masayoshi KOBAYASHI ,  Takeo ODA ,  Ryusuke MATSUYAMA ,  Atsushi HORIKAWA ,  Hitoshi FUJIWARA

    IPC: F23R3/28

    CPC classification number: F23R3/28 ,  F23R3/14 ,  F23R3/16 ,  F23R3/18 ,  F23R3/286 ,  F23R3/343 ,  F23R3/50

    Abstract: An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.

    Abstract translation: 在圆周上具有多个燃料喷嘴组件（10）的环形燃气轮机燃烧器包括用于将用于扩散燃烧的燃料从先导外周喷嘴（34）喷射到燃烧室（8）中的先导喷嘴单元（12） 设置为围绕用于预混燃烧的燃料喷射的先导喷嘴单元（12）设置的主喷嘴单元（14），以及设置在每个燃料喷嘴组件（10）的下游侧的流动引导件（27） 并且具有从下游方向逐渐增加的每个燃料喷嘴组件（10）的空气和空气 - 燃料混合物的通道的截面面积。

    FUEL INJECTION DEVICE
    6.
    发明申请
    FUEL INJECTION DEVICE 审中-公开
    燃油喷射装置

    公开(公告)号：US20150082797A1

    公开(公告)日：2015-03-26

    申请号：US14557877

    申请日：2014-12-02

    Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA ,  JAPAN AEROSPACE EXPLORATION AGENCY

    Inventor： Ryusuke MATSUYAMA ,  Masayoshi KOBAYASHI ,  Atsushi HORIKAWA ,  Hitoshi FUJIWARA

    IPC: F23R3/16 ,  F23R3/18 ,  F23R3/34

    CPC classification number: F23R3/16 ,  F23R3/14 ,  F23R3/18 ,  F23R3/28 ,  F23R3/34 ,  F23R3/343 ,  Y02T50/675

    Abstract: A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis.

    Abstract translation: 用于向压缩空气供给燃料的燃料喷射装置包括：先导燃料喷射器; 主燃料喷射器，位于引燃燃料喷射器的外周; 以及位于先导燃料喷射器的出口端部与主燃料喷射器之间的空气喷射单元。 空气喷射单元包括：分隔壁板，其将空气喷射单元与燃烧室分离; 设置在隔壁板的下游侧的火焰稳定板; 在火焰稳定板和引燃燃料喷射器的出口端部之间的下游侧的第一开口; 以及设置在分隔壁板中的第二开口，通过该第二开口供应压缩空气。 火焰稳定板包括相对于轴线沿径向向外和向下游方向倾斜的倾斜部分。

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