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    Mixer assembly for gas turbine engine
    1.
    发明专利
    Mixer assembly for gas turbine engine 有权
    燃气轮机发动机混合器总成

    公开(公告)号：JP2012154618A

    公开(公告)日：2012-08-16

    申请号：JP2012010601

    申请日：2012-01-23

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： DAI ZHONGTAO ,  COHEN JEFFREY M ,  FOTACHE CATALIN G

    IPC: F23R3/18 ,  F02C7/24 ,  F23R3/06 ,  F23R3/14 ,  F23R3/30

    CPC classification number: F23R3/343 ,  F23R3/14 ,  F23R3/18 ,  F23R3/286 ,  Y02T50/675

    Abstract: PROBLEM TO BE SOLVED: To provide a mixer assembly 200 for a gas turbine engine 10.SOLUTION: The mixer assembly 200 includes a main mixer 220 and a pilot mixer 210 concentrically arranged with respect to the main mixer. The main mixer encloses at least part of the pilot mixer. The pilot mixer includes an annular housing 212 defining a cavity 208 to be partitioned from the main mixer. The housing has a front portion 202 and a rear portion 204, a diameter of the rear portion being larger than that of the front portion. The pilot mixer further includes a fuel nozzle 152 enclosed by the front portion of the housing and a partition 214 located downstream of the nozzle and connecting the front portion to the rear portion of the housing. The partition 214 is substantially perpendicular to the rear portion 204 of the housing and defines a corner 206 between the rear portion and the partition.

    Abstract translation: 要解决的问题：提供一种用于燃气涡轮发动机10的混合器组件200.解决方案：混合器组件200包括主混合器220和相对于主混合器同心布置的先导混合器210。 主混合器至少包含一部分先导混合器。 导向混合器包括限定要从主混合器分隔的空腔208的环形壳体212。 壳体具有前部202和后部204，后部的直径大于前部的直径。 先导式混合器还包括由壳体的前部包围的燃料喷嘴152和位于喷嘴下游并将前部连接到壳体的后部的分隔件214。 分隔件214基本上垂直于壳体的后部204并且在后部和分隔件之间限定了角部206。 版权所有（C）2012，JPO＆INPIT

    AXIAL STAGED COMBUSTOR WITH RESTRICTED MAIN FUEL INJECTOR
    2.
    发明申请
    AXIAL STAGED COMBUSTOR WITH RESTRICTED MAIN FUEL INJECTOR 审中-公开
    带有限制的主燃料喷射器的轴式燃烧器

    公开(公告)号：WO2015147951A3

    公开(公告)日：2015-11-19

    申请号：PCT/US2015010082

    申请日：2015-01-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAI ZHONGTAO ,  HOLLEY ADAM TAKASHI ,  MCKINNEY RANDAL G

    IPC: F23R3/28 ,  F02C7/22 ,  F23R3/30

    CPC classification number: F23R3/346 ,  F02C3/04 ,  F05D2220/32 ,  F23D14/70 ,  F23R3/12 ,  F23R3/286 ,  F23R3/343

    Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的燃烧器包括燃烧室，其具有在一端的先导喷射器和与引燃喷射器径向间隔开的至少一个主喷射器。 主喷射器包括具有塞子的流体流动路径，其至少在流动路径的内部部分限制流动。 还公开了一种燃气涡轮发动机。

    FUEL AIR PREMIXER FOR GAS TURBINE ENGINE
    5.
    发明专利
    FUEL AIR PREMIXER FOR GAS TURBINE ENGINE 未知

    公开(公告)号：SG11201405495PA

    公开(公告)日：2014-11-27

    申请号：SG11201405495P

    申请日：2013-02-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAI ZHONGTAO ,  COHEN JEFFREY M ,  GREEN KEVIN E

    IPC: F23R3/14 ,  F02C7/22 ,  F02K99/00 ,  F23R3/42

    Abstract: A fuel-air premixer for a combustor of a turbine engine includes a central passage along an axis. The central passage is operable to communicate an unswirled airflow. An outer annular passage is located around the axis and includes a multiple of first swirl vanes that are operable to communicate a first swirled airflow in a first direction. An inner annular passage is located around the axis between the central passage and the outer annular passage. The inner annular passage includes a multiple of second swirl vanes that are operable to communicate a second swirled airflow in a second direction different than the first direction.

    FUEL AIR PREMIXER FOR GAS TURBINE ENGINE
    6.
    发明公开
    FUEL AIR PREMIXER FOR GAS TURBINE ENGINE 审中-公开
    用于燃气涡轮发动机的燃料空气预混合器

    公开(公告)号：EP2825824A4

    公开(公告)日：2015-10-28

    申请号：EP13760976

    申请日：2013-02-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAI ZHONGTAO ,  COHEN JEFFREY M ,  GREEN KEVIN E

    IPC: F23R3/28 ,  F02C7/22 ,  F02K3/00 ,  F02K99/00 ,  F23R3/14 ,  F23R3/42

    CPC classification number: F23R3/14 ,  F23R3/28 ,  Y02T50/675

    Abstract: A fuel-air premixer for a combustor of a turbine engine includes a central passage along an axis. The central passage is operable to communicate an unswirled airflow. An outer annular passage is located around the axis and includes a multiple of first swirl vanes that are operable to communicate a first swirled airflow in a first direction. An inner annular passage is located around the axis between the central passage and the outer annular passage. The inner annular passage includes a multiple of second swirl vanes that are operable to communicate a second swirled airflow in a second direction different than the first direction.

    DUAL FUEL NOZZLE SYSTEM AND APPARATUS
    9.
    发明公开
    DUAL FUEL NOZZLE SYSTEM AND APPARATUS 审中-公开
    ZWEISTOFFDÜSENSYSTEMSOWIE VORRICHTUNG

    公开(公告)号：EP3036482A4

    公开(公告)日：2017-05-03

    申请号：EP14838205

    申请日：2014-08-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER TIMOTHY S ,  DAI ZHONGTAO ,  SMITH RANDOLPH J ,  KOPP-VAUGHAN KRISTIN

    IPC: F23R3/36 ,  F02C7/22 ,  F23R3/28

    CPC classification number: F23C1/08 ,  F23D14/48 ,  F23D2900/11101 ,  F23R3/286 ,  F23R3/36

    Abstract: In various embodiments, a dual fuel nozzle (200) for use in a gas 200 turbine engine is provided. The nozzle may be configured to supply and gas and a liquid. The dual fuel nozzle (200) may include an interior wall (217). The interior wall (217) may include a shoulder (219). The shoulder (219) may include one or more gas ports (216). Gas may be discharged through the gas ports (216) and penetrate a mixing zone.

    Abstract translation: 在各种实施例中，提供了用于气体涡轮机200中的双燃料喷嘴（200）。 喷嘴可以被构造成供应气体和液体。 双燃料喷嘴（200）可以包括内壁（217）。 内壁（217）可以包括肩部（219）。 肩部（219）可以包括一个或多个气体端口（216）。 气体可以通过气体端口（216）排出并穿过混合区域。

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