利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

43 条记录 (耗时 0.016 秒)

    Gas turbine combustor with improved quench holes arrangement
    34.
    发明公开
    Gas turbine combustor with improved quench holes arrangement 审中-公开
    具有擦除孔的改进布置的燃气涡轮机燃烧器

    公开(公告)号：EP2290289A3

    公开(公告)日：2014-10-15

    申请号：EP10251531.9

    申请日：2010-08-31

    申请人： United Technologies Corporation

    发明人： Snyder, Timothy S. ,  Kim, Won-Wook

    IPC分类号： F23R3/06 ,  F23R3/50

    CPC分类号： F23R3/06 ,  F23R3/50 ,  Y02T50/675

    摘要： A gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a plurality of smaller quench air admission holes (120) disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes (120) are arranged with respect to the plurality of relatively large dilution air admission holes (116) disposed upstream thereof such that there is associated with each dilution air admission hole (116) a first quench air admission hole (120) and a second quench air admission hole (120), the first quench air admission hole (120) being offset laterally in a first lateral direction and the second quench air admission hole (120) being offset laterally in a second lateral direction opposite to the first direction.

    Advanced quench pattern combustor
    35.
    发明公开
    Advanced quench pattern combustor 审中-公开
    燃烧室与擦除孔的改进布置

    公开(公告)号：EP2253887A3

    公开(公告)日：2014-08-20

    申请号：EP10163039.0

    申请日：2010-05-17

    申请人： United Technologies Corporation

    发明人： Kim, Won-Wook ,  Snyder, Timothy S.

    IPC分类号： F23R3/06

    CPC分类号： F23R3/06

    摘要： A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.

    Hooded air/fuel swirler for a gas turbine engine
    36.
    发明公开
    Hooded air/fuel swirler for a gas turbine engine 有权
    Luft- / Brennstoffdrallerzeuger mit HaubefürGasturbinenmotoren

    公开(公告)号：EP1978306A2

    公开(公告)日：2008-10-08

    申请号：EP08250535.5

    申请日：2008-02-14

    申请人： United Technologies Corporation

    发明人： Snyder, Timothy S.

    IPC分类号： F23R3/14

    CPC分类号： F23R3/14

    摘要： A gas turbine engine pilot assembly includes a swirler (28) having high and low pressure sides (12, 14). A hood (32) at least partially encloses the swirler (28) on the high pressure side (12). The hood (32) is secured over the swirler (28), in one example. The hood (32) includes an aperture creating a tortuous path from the high pressure side (12) to the low pressure side (14) through the swirler (28). The hood (32) reduces the differential pressure across the swirler (28) by reducing the velocity and pressure of the air before entering the swirler (28). In one example, the hood (32) includes first and second spaced apart walls (38, 40) interconnected by a perimeter wall (36). The walls (38, 40, 36) form a generally annular structure, in one example. At least one of the walls (38, 40, 36) includes an array of apertures (42, 44) communicating with a cavity interiorly arranged within the walls (38, 40, 36) upstream from the swirler (28). Air from the high pressure side (12) flows through the apertures (42, 44) and is slowed before passing through the swirler (28) and into a combustion chamber (20).

    摘要翻译： 燃气涡轮发动机引导组件包括具有高低压侧（12,14）的旋流器（28）。 罩（32）至少部分地包围在高压侧（12）上的旋流器（28）。 在一个示例中，罩（32）固定在旋流器（28）上。 罩（32）包括通过旋流器（28）产生从高压侧（12）到低压侧（14）的曲折路径的孔。 发动机罩（32）通过在进入旋流器（28）之前降低空气的速度和压力来减小旋流器（28）两端的差压。 在一个示例中，罩（32）包括通过周边壁（36）互连的第一和第二隔开的壁（38,40）。 在一个示例中，壁（38,40,36）形成大致环形结构。 壁（38,40,36）中的至少一个包括与腔室（38,40,36）内部布置在旋流器（28）上游的壁（38,40,36）内连通的孔的阵列。 来自高压侧（12）的空气流过孔（42,44），并在通过旋流器（28）并进入燃烧室（20）之前减慢。

    Fuel nozzle
    37.
    发明公开
    Fuel nozzle 有权
    燃油喷嘴

    公开(公告)号：EP1424526A3

    公开(公告)日：2007-04-04

    申请号：EP03257053.3

    申请日：2003-11-07

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Snyder, Timothy S. ,  Hoke, James B.

    IPC分类号： F23R3/28 ,  F23D11/10 ,  F23D11/24

    CPC分类号： F23R3/28 ,  F23D11/10 ,  F23D11/24 ,  F23D2900/00016 ,  F23D2900/11101

    摘要： The present invention relates to a fuel nozzle (10) for use in an engine such as a gas turbine engine. The fuel nozzle (10) includes a fuel injector (14) for injecting fuel into a combustion chamber of the engine and a plurality of rows (16,18) of holes (20) surrounding the fuel injector (14) for eliminating recirculation of hot gas products onto a face of the fuel nozzle. The holes (20) eject air primarily in an axial direction.

    摘要翻译： 本发明涉及用于诸如燃气涡轮发动机的发动机中的燃料喷嘴（10）。 燃料喷嘴（10）包括用于将燃料喷射到发动机的燃烧室中的燃料喷射器（14）和包围燃料喷射器（14）的多个孔（20,18）的排（16,18），用于消除热的再循环 气体产品喷射到燃料喷嘴的表面上。 孔（20）主要沿轴向喷射空气。

    Fuel nozzle
    39.
    发明公开
    Fuel nozzle 有权
    Brennstoffeinspritzdüse

    公开(公告)号：EP1424526A2

    公开(公告)日：2004-06-02

    申请号：EP03257053.3

    申请日：2003-11-07

    申请人： United Technologies Corporation

    发明人： Snyder, Timothy S. ,  Hoke, James B.

    IPC分类号： F23R3/28

    CPC分类号： F23R3/28 ,  F23D11/10 ,  F23D11/24 ,  F23D2900/00016 ,  F23D2900/11101

    摘要： The present invention relates to a fuel nozzle (10) for use in an engine such as a gas turbine engine. The fuel nozzle (10) includes a fuel injector (14) for injecting fuel into a combustion chamber of the engine and a plurality of rows (16,18) of holes (20) surrounding the fuel injector (14) for eliminating recirculation of hot gas products onto a face of the fuel nozzle. The holes (20) eject air primarily in an axial direction.

    摘要翻译： 本发明涉及一种用于诸如燃气涡轮发动机的发动机中的燃料喷嘴（10）。 燃料喷嘴（10）包括用于将燃料喷射到发动机的燃烧室中的燃料喷射器（14）和围绕燃料喷射器（14）的多个排（16,18）的孔（16,18），用于消除热的再循环 气体产品放在燃料喷嘴的表面上。 孔（20）主要沿轴向排出空气。

    Low emissions combustor for a gas turbine engine
    40.
    发明公开
    Low emissions combustor for a gas turbine engine 有权
    燃烧室具有低排放的燃气涡轮机

    公开(公告)号：EP1235032A3

    公开(公告)日：2004-01-21

    申请号：EP02251341.0

    申请日：2002-02-26

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Snyder, Timothy S.

    IPC分类号： F23R3/06 ,  F23R3/00

    CPC分类号： F23R3/002 ,  F23R3/06 ,  Y02T50/675

    摘要： A combustor for a gas turbine engine includes inner and outer liners 32,34 with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner 34 comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer holes 118 circumferentially intermediate neighboring pairs of the major outer holes 116. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes 116 and may also include a set of minor holes 122 circumferentially intermediate major inner holes 120 . The major and minor holes admit respective major and minor jets of dilution air into the combustor. The distribution of major and minor holes and the corresponding major and minor dilution air jets helps to minimize NOx emissions and regulates the spatial temperature profile of the exhaust gases discharged from the combustor.