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    Gas Turbine Combustor
    12.
    发明公开
    Gas Turbine Combustor 有权
    燃气轮机燃烧室

    公开(公告)号：EP2492597A2

    公开(公告)日：2012-08-29

    申请号：EP12160964.8

    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.

    Abstract translation: 用于燃气轮机的环形燃烧器（100）具有燃烧室，燃烧室具有内部容积，该内部容积在纵向截面中包括前部容积（V1），中间容积（V2）和后部容积（V3）。 前部容积（V1）表示燃烧室内部容积的约30％至约40％，中间容积（V2）表示燃烧室内部容积的约10％至约20％，并且后部容积（V3）表示 从燃烧室内部容积的约40％至约60％。

    Gas turbine combustor
    14.
    发明公开
    Gas turbine combustor 审中-公开

    公开(公告)号：EP1775516A3

    公开(公告)日：2010-06-30

    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.

    Local cooling hole pattern
    15.
    发明公开
    Local cooling hole pattern 有权
    LokalesKühllochmuster

    公开(公告)号：EP1798474A2

    公开(公告)日：2007-06-20

    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.

    Abstract translation: 燃烧器组件包括限定燃烧室的内衬套和外衬套。 内衬套和外衬套包括间隔开特定距离的多个冷却孔。 冷却孔包括规定的倾斜角（54）和圆周角（56）。 冷却孔的第一组（58）根据均匀的几何图形和密度间隔开。 设置在衬套组件内的第一组（58）和一些结构特征（32; 38; 40）之间的第二组（62; 68; 72）以不均匀的图案和等于 第一组冷却孔。 不均匀的冷却孔布置提高了冷却流动效率，以适应局部干扰和热性能。

    Swirler, fuel and air assembly and combustor
    19.
    发明公开
    Swirler, fuel and air assembly and combustor 审中-公开
    旋转器，燃料和空气组件和硝基

    公开(公告)号：EP2400220A3

    公开(公告)日：2015-07-22

    申请号：EP11250606.8

    申请日：2011-06-23

    Applicant: United Technologies Corporation

    Inventor： Cheung, Albert K.

    IPC: F23R3/14 ,  F23R3/34 ,  F23R3/28

    CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R3/34

    Abstract: An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed.
    The air swirler (20) has a number of air passages (76, 78), and the air in the different passages can be made to swirl in different directions to improve mixing. The fuel and air assembly has inner and outer fuel ports, which allow fuel to be introduced to different regions of the assembly at the same time. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability.

    Gas Turbine Combustor
    20.
    发明公开
    Gas Turbine Combustor 有权
    燃气轮机燃烧室

    公开(公告)号：EP2492597A3

    公开(公告)日：2014-01-08

    申请号：EP12160964.8

    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.

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