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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

    FUEL SYSTEM AND METHOD OF REDUCING EMISSION
    2.
    发明专利
    FUEL SYSTEM AND METHOD OF REDUCING EMISSION 未知

    公开(公告)号：SG131865A1

    公开(公告)日：2007-05-28

    申请号：SG2006069876

    申请日：2006-10-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHEN ALEXANDER G ,  COHEN JEFFREY M

    Abstract: A fuel system (22; 10') includes a fuel deoxygenator (26) for removing oxygen from a liquid fuel. A vaporizer (30) is in fluid communication with the fuel deoxygenator (26). The vaporizer (30) vaporizes at least a portion of the liquid fuel to produce vaporized fuel. At least a portion of the vaporized fuel pre-mixes with oxidizer (33) to reduce formation of undesirable emissions.

    FUEL AIR PREMIXER FOR GAS TURBINE ENGINE
    4.
    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.

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