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    COMBUSTION DEVICE FOR GAS TURBINE ENGINE
    3.
    发明申请
    COMBUSTION DEVICE FOR GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机燃烧装置

    公开(公告)号：US20170074521A1

    公开(公告)日：2017-03-16

    申请号：US15363105

    申请日：2016-11-29

    申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA

    发明人： Atsushi HORIKAWA ,  Masahide KAZARI ,  Kunio OKADA ,  Junichi KITAJIMA

    IPC分类号： F23R3/28 ,  F23R3/00

    CPC分类号： F23R3/286 ,  F02C7/232 ,  F23C2900/9901 ,  F23D2209/20 ,  F23R3/002 ,  F23R3/16 ,  F23R3/28 ,  F23R3/283 ,  F23R3/30 ,  F23R3/32 ,  F23R3/34 ,  F23R2900/03044 ,  Y02T50/675 ,  Y02T50/678

    摘要： A combustor includes: a combustion liner having a combustion chamber formed therein; a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion; and a supplemental burner. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide groove that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

    摘要翻译： 燃烧器包括：具有形成在其中的燃烧室的燃烧衬套; 燃料喷射器，其安装到燃烧衬套的顶部，并且包括具有多个燃料喷射环形部分的燃料喷射构件和包括引导空气用于燃烧的多个燃烧空气环形部分的空气引导构件; 和补充燃烧器。 燃料喷射环形部分和燃烧空气环形部分同心地和交替地布置。 燃料喷射器将燃料和空气喷射到燃烧室中。 每个燃料喷射环形部分包括沿其径向开口的多个燃料喷射孔，并且每个燃烧空气环形部分包括在其轴向方向上敞开的多个空气引导槽，并且引导 从燃料喷射孔喷射的燃料的空气。

    LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE
    5.
    发明申请
    LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE 审中-公开
    具有用于气体涡轮机的氧气去除气体（ODG）注射系统的液体燃料燃烧器

    公开(公告)号：US20160053681A1

    公开(公告)日：2016-02-25

    申请号：US14464032

    申请日：2014-08-20

    申请人： General Electric Company

    发明人： William Francis Carnell, JR. ,  Ilya Aleksandrovich Slobodyanskiy

    IPC分类号： F02C3/24 ,  F23R3/30 ,  F02C3/34

    CPC分类号： F23R3/30 ,  F02C3/34 ,  F23C9/006 ,  F23C2202/30 ,  F23R3/16

    摘要： A liquid fuel combustor for a gas turbomachine includes a combustor body, a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. A nozzle is arranged at the head end of the combustor liner. The nozzle includes a first inlet, a second inlet and an outlet configured and disposed to establish a flame zone. The first inlet is configured to receive a first fluid and the second inlet is configured to receive a second fluid. The second fluid includes a liquid fuel. An oxygen-depleted gas (ODG) injection system is arranged radially outwardly of the nozzle. The ODG injection system is configured and disposed to deliver an oxygen-depleted gas stream into the combustion chamber to vaporize a portion of the second fluid.

    摘要翻译： 用于气体涡轮机的液体燃料燃烧器包括燃烧器主体，布置在燃烧器主体中的燃烧器衬套，其限定从头端延伸到燃烧器排放口的燃烧室。 燃烧器衬套与燃烧器主体间隔开，形成压缩机排气壳（CDC）气流通道。 喷嘴位于燃烧器衬套的头端。 喷嘴包括构造和设置成建立火焰区的第一入口，第二入口和出口。 第一入口构造成接收第一流体，并且第二入口构造成接收第二流体。 第二流体包括液体燃料。 耗氧气体（ODG）注射系统布置在喷嘴的径向外侧。 配置和设置ODG注射系统以将贫氧气流输送到燃烧室中以蒸发第二流体的一部分。

    Gas Turbine Combustor
    6.
    发明申请
    Gas Turbine Combustor 审中-公开
    燃气轮机燃烧器

    公开(公告)号：US20160010864A1

    公开(公告)日：2016-01-14

    申请号：US14772535

    申请日：2013-03-13

    申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.

    发明人： Kazuki ABE ,  Tomomi KOGANEZAWA ,  Keisuke MIURA

    IPC分类号： F23R3/12 ,  F23R3/28

    CPC分类号： F23R3/12 ,  F23R3/28 ,  F23R3/286 ,  F23R3/30 ,  F23R3/32 ,  F23R3/343 ,  F23R3/346

    摘要： In a perforated coaxial jet burner implemented by a lot of air-fuel coaxial jets, a swirl plate (33) as an end face of the burner on the combustion chamber's side has a lot of air holes for supplying unburned premixed gas of fuel and air to the combustion chamber. Grooves (36) are formed downstream of the air holes of the swirl plate. Adhesion of flame to the swirl plate is inhibited by feeding part of the unburned premixed gas to the grooves. Further, the width of each remaining part (37) between adjacent grooves is set at several millimeters that is approximately equal to the flame quenching distance, by which adhesion of flame to the remaining parts is also prevented. With this configuration, both stable combustion and low NOx combustion can be achieved irrespective of the load condition.

    摘要翻译： 在由许多空气 - 燃料同轴射流器实现的穿孔同轴喷气燃烧器中，作为燃烧室侧的燃烧器端面的旋流板（33）具有大量用于供应未燃燃料和空气的预混气体的气孔 到燃烧室。 沟槽（36）形成在涡流板的气孔的下游。 通过将部分未燃烧的预混合气体供应到凹槽来阻止火焰对涡旋板的粘附。 此外，相邻槽之间的每个剩余部分（37）的宽度被设定为大约等于火焰熄灭距离的几毫米，由此也阻止了火焰与其余部分的粘附。 利用这种构造，可以实现稳定燃烧和低NOx燃烧，而与负载条件无关。

    Supercritical or mixed phase fuel injector
    7.
    发明授权
    Supercritical or mixed phase fuel injector 有权
    超临界或混合燃料喷射器

    公开(公告)号：US09222676B2

    公开(公告)日：2015-12-29

    申请号：US13336670

    申请日：2011-12-23

    申请人： Timothy C. Roesler

    发明人： Timothy C. Roesler

    IPC分类号： F23R3/30 ,  F02C9/28 ,  F02C9/48 ,  F23K5/14 ,  F23N1/00

    CPC分类号： F23R3/30 ,  F02C9/28 ,  F02C9/48 ,  F23K5/14 ,  F23K2301/10 ,  F23K2301/20 ,  F23N1/002 ,  F23N2041/20

    摘要： An apparatus is disclosed including a main fuel supply fluidly coupled to a main fuel valve and an arcuate fuel passage receiving main fuel through the main fuel valve. The arcuate fuel passage includes a passage diameter and a radius of curvature which provides sufficient rotational acceleration to the main fuel such that a liquid portion of the main fuel is deposited on an outer wall of the arcuate fuel passage. The apparatus includes a fuel injector nozzle that receives the main fuel from the arcuate fuel passage, and injects the main fuel into a combustion chamber for a turbine engine. The apparatus further includes a pilot fuel supply fluidly coupled to a pilot fuel passage and a fuel selector structured to selectively provide the main fuel or the pilot fuel to the fuel injector nozzle.

    摘要翻译： 公开了一种装置，其包括流体地联接到主燃料阀的主燃料供应器和通过主燃料阀接收主燃料的弓形燃料通道。 弓形燃料通道包括通道直径和曲率半径，其向主燃料提供足够的旋转加速，使得主燃料的液体部分沉积在弓形燃料通道的外壁上。 该装置包括燃料喷射器喷嘴，其从弓形燃料通道接收主燃料，并将主燃料喷射到用于涡轮发动机的燃烧室中。 该设备还包括流体地联接到引燃燃料通道的引燃燃料供应器和构造成选择性地将燃料或引燃燃料提供给燃料喷射器喷嘴的燃料选择器。

    TWO-CIRCUIT INJECTOR FOR A TURBINE ENGINE COMBUSTION CHAMBER
    8.
    发明申请
    TWO-CIRCUIT INJECTOR FOR A TURBINE ENGINE COMBUSTION CHAMBER 有权
    用于涡轮发动机燃烧室的两电路喷射器

    公开(公告)号：US20150260406A1

    公开(公告)日：2015-09-17

    申请号：US14432952

    申请日：2013-09-23

    申请人： TURBOMECA

    发明人： Bernard Carrere

    IPC分类号： F23R3/30 ,  F23R3/34 ,  F02C7/264 ,  F02C3/14

    CPC分类号： F23R3/30 ,  F02C3/14 ,  F02C7/264 ,  F23D11/446 ,  F23R3/343 ,  Y02T50/671

    摘要： A start-up injector for a turbine engine combustion chamber, said injector including a fuel injection circuit; and a fuel ignition circuit including a fuel injector supplied by the fuel injection circuit and a spark plug for igniting the injected fuel. The start-up injector also includes a partitioned enclosure including a first compartment in which the fuel is ignited by the spark plug and a second compartment separated from the first compartment by a thermally conductive partition; and a main combustion start-up circuit which includes at least one fuel injector supplied by the fuel injection circuit and opens into the second compartment of the enclosure such as to inject the fuel against the wall.

    摘要翻译： 一种用于涡轮发动机燃烧室的起动注射器，所述喷射器包括燃料喷射回路; 以及包括由燃料喷射回路供给的燃料喷射器和用于点燃喷射燃料的火花塞的燃料点火电路。 启动注射器还包括分隔的外壳，其包括第一隔间，燃料由火花塞点燃，第二隔室通过导热隔板与第一隔间隔开; 以及主燃烧起动电路，其包括由所述燃料喷射回路供应并且通向所述外壳的所述第二隔室中的至少一个燃料喷射器，以将所述燃料喷射到所述壁上。