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    Gas turbine combustor
    2.
    发明公开
    Gas turbine combustor 有权

    公开(公告)号：EP2503245A3

    公开(公告)日：2014-01-15

    申请号：EP12160966.3

    申请日：2010-11-24

    Applicant: United Technologies Corporation

    Inventor： Hoke, James B. ,  Cheung, Albert K. ,  Sowa, William A.

    IPC: F23R3/50 ,  F23R3/06

    CPC classification number: F23R3/50 ,  F23R3/06 ,  Y02T50/675

    Abstract: An annular combustor (100) for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume (V 1 ), an intermediate volume (V 2 ) and an aft volume (V 3 ). The forward volume (V 1 ) represents from about 30% to about 40% of the combustor interior volume, the intermediate volume (V 2 ) represents from about 10% to about 20% of the combustor interior volume, and the aft volume (V 3 ) represents from about 40% to about 60% of the combustor interior volume.

    Gas turbine combustor
    4.
    发明公开
    Gas turbine combustor 审中-公开
    燃气轮机燃烧室

    公开(公告)号：EP1775516A2

    公开(公告)日：2007-04-18

    申请号：EP06255344.1

    申请日：2006-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W. ,  Sowa, William ,  Cheung, Albert K. ,  Kramer, Stephen K. ,  Hokes, James ,  Smith, Reid Dyer Curtis

    IPC: F23R3/50

    CPC classification number: F23R3/50

    Abstract: A combustor assembly (12) includes a convergent segment (34) followed by a divergent segment (36) to advantageously improve combustion. The combustor assembly includes a first segment (34) beginning at a forward end (24) that transitions to a second segment (36) past a transition segment (58) in a direction along a combustor axis (22) toward an aft end (26). The reduction in cross-sectional area within the first segment (34) provides desirable fuel and air mixing properties. The convergent first segment (34) in combination with the divergent second segment (36) decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

    Abstract translation: 一个燃烧器组件（12）包括一个收敛段（34），后面跟着一个扩张段（36），以有利地改善燃烧。 燃烧器组件包括在前端（24）开始的第一部分（34），该第一部分在沿着燃烧器轴线（22）的方向上朝向后端（26）过渡到经过过渡部分（58）的第二部分（36） ）。 第一段（34）内的横截面积的减小提供了期望的燃料和空气混合特性。 会聚的第一部分（34）与发散的第二部分（36）结合减少了燃烧室内燃料 - 空气混合物的停留时间，这减少了来自燃烧室组件的不希望的排放物的产生。

    Swirler for gas turbine engine fuel injector
    5.
    发明公开
    Swirler for gas turbine engine fuel injector 审中-公开
    DrallerzeugerfürBrennstoffeinspritzeinrichtung eines Gasturbinen Motors

    公开(公告)号：EP2541148A3

    公开(公告)日：2017-04-19

    申请号：EP12172282.1

    申请日：2012-06-15

    Applicant: United Technologies Corporation

    Inventor： Cheung, Albert K.

    IPC: F23R3/14 ,  F23R3/28

    Abstract: A swirler (50;80) for fuel injection in a gas turbine engine (10) includes a frustoconical swirler body (51). First and a second air flow paths (52,54;82) direct air in generally opposed circumferential directions into the swirler (50;80). These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body (51). In a separate feature, a third air flow path (56;84) is directed into the air.

    Abstract translation: 在燃气涡轮发动机（10）中用于燃料喷射的旋流器（50; 80）包括截头圆锥形旋流器主体（51）。 第一和第二空气流动路径（52,54; 82）将大致相对的圆周方向的空气引导到旋流器（50; 80）中。 这些气道混合并产生湍流。 当这种湍流遇到燃料液滴时，燃料被雾化，并且均匀分布在空气流中。 在旋流器主体（51）的内表面附近形成剪切层。 在单独的特征中，第三气流路径（56; 84）被引导到空气中。

    Swirler for gas turbine engine fuel injector
    6.
    发明公开
    Swirler for gas turbine engine fuel injector 审中-公开
    涡旋发生器用于燃气涡轮发动机的燃料喷射器

    公开(公告)号：EP2541148A2

    公开(公告)日：2013-01-02

    申请号：EP12172282.1

    申请日：2012-06-15

    Applicant: United Technologies Corporation

    Inventor： Cheung, Albert K.

    IPC: F23R3/14 ,  F23R3/28

    Abstract: A swirler (50;80) for fuel injection in a gas turbine engine (10) includes a frustoconical swirler body (51). First and a second air flow paths (52,54;82) direct air in generally opposed circumferential directions into the swirler (50;80). These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body (51). In a separate feature, a third air flow path (56;84) is directed into the air.

    Local cooling hole pattern
    8.
    发明公开
    Local cooling hole pattern 有权
    局部冷却孔图案

    公开(公告)号：EP1798474A3

    公开(公告)日：2010-06-30

    申请号：EP06256259.0

    申请日：2006-12-08

    Applicant: United Technologies Corporation

    Inventor： Burd, Steven W. ,  Cheung, Albert K.

    IPC: F23R3/06

    CPC classification number: F23R3/06

    Abstract: A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle (54) and circumferential angle (56). A first group (58) of cooling holes is spaced apart according to a uniform geometric pattern and density. A second group (62; 68; 72) disposed between the first group (58) and some structural feature (32; 38; 40) within the liner assembly is disposed at a non-uniform pattern and a hole density equal to the density of the first group of cooling holes. The non-uniform cooling hole arrangement increases cooling flow effectiveness to accommodate local disturbances and thermal properties.

    Hole pattern for gas turbine combustor
    9.
    发明公开
    Hole pattern for gas turbine combustor 审中-公开
    LochmusterfürGasturbinenbrennkammer

    公开(公告)号：EP2133628A2

    公开(公告)日：2009-12-16

    申请号：EP09250924.9

    申请日：2009-03-30

    Applicant: United Technologies Corporation

    Inventor： Shelley, Jonathan K. ,  Burd, Steven W. ,  Cheung, Albert K. ,  Kozola, Stuart L.

    IPC: F23R3/06

    CPC classification number: F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A combustor for a turbine engine includes an outer liner (34) having a row of circumferentially distributed outer combustion air holes and an inner liner (32) circumscribed by the outer liner (34) and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners (32, 34) each include at least a major air hole (104) having a first hole size, an intermediate air hole (108) having a second hole size, and a minor air hole (106) having a third hole size. The first, second, and third hole sizes are all different from each other.

    Abstract translation: 用于涡轮发动机的燃烧器包括具有一排周向分布的外部燃烧气孔的外衬套（34​​）和由外衬套（34​​）外接的内衬（32），并且具有一排周向分布的内燃气孔。 内衬层和外衬层（32,34）各自至少包括具有第一孔尺寸的主空气孔（104），具有第二孔尺寸的中间空气孔（108）和具有第二孔尺寸的小空气孔（106） 第三洞大小。 第一，第二和第三孔的尺寸都是不同的。

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