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13 条记录 (耗时 0.015 秒)

    Transition nozzle combustion system
    1.
    发明授权
    Transition nozzle combustion system 有权
    过渡喷嘴燃烧系统

    公开(公告)号：US09506359B2

    公开(公告)日：2016-11-29

    申请号：US13437953

    申请日：2012-04-03

    申请人： Won-Wook Kim ,  Kevin Weston McMahan ,  Jaime Javier Maldonado

    发明人： Won-Wook Kim ,  Kevin Weston McMahan ,  Jaime Javier Maldonado

    IPC分类号： F01D9/02

    CPC分类号： F01D9/023 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

    摘要： The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

    摘要翻译： 本申请提供了一种用于冷却流的燃烧系统。 燃烧系统可以包括头端，后端，从头端延伸到后端的过渡喷嘴和围绕过渡喷嘴的冲击套筒。 冲击套筒可以限定与头端连通的用于冷却流的第一部分的第一空腔和与后端连通的用于冷却流的第二部分的第二空腔。 过渡喷嘴可以包括与冷却流的第二部分连通的多个冷却孔。

    Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor
    3.
    发明授权
    Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor 有权
    用于燃气轮机发动机燃烧器的局部共旋流淬火喷射模式的温度混合增强

    公开(公告)号：US09322554B2

    公开(公告)日：2016-04-26

    申请号：US13194182

    申请日：2011-07-29

    申请人： Won-Wook Kim ,  James B. Hoke ,  Timothy S. Snyder

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

    IPC分类号： F02C1/00 ,  F23R3/06 ,  F23R3/08

    CPC分类号： F23R3/06 ,  F23R3/08 ,  Y02T50/675

    摘要： A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.

    摘要翻译： 用于涡轮发动机的燃烧器包括围绕具有第一排第一燃烧空气孔的轴限定的第一衬套，沿着多个燃料喷射器零间距线中的每一个限定第一燃烧空气孔中的一个。 围绕所述轴限定第二排第二燃烧空气孔的第二衬套，每个所述第二燃烧空气孔相对于所述多个燃料喷射器零间距线中的每一个周向地偏移。

    Gas turbine combustor with quench wake control
    4.
    发明授权
    Gas turbine combustor with quench wake control 有权
    燃气轮机燃烧器具有淬火尾流控制

    公开(公告)号：US08739546B2

    公开(公告)日：2014-06-03

    申请号：US12550845

    申请日：2009-08-31

    申请人： Timothy S. Snyder ,  Won-Wook Kim

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

    IPC分类号： F02C1/00 ,  F02G3/00

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

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

    摘要翻译： 燃气涡轮发动机具有燃烧器模块，该燃烧器模块包括环形燃烧器，该环形燃烧器具有限定环形燃烧室的衬套组件，并且包括周向排的多个相对较大的燃烧稀释空气进入孔和周向排的多个较小的骤冷空气入口 相对于燃烧气体产物的流动设置在下游的孔。 多个骤冷空气入口相对于设置在其上游的多个相对较大的稀释空气进入孔布置，使得与每个稀释空气入口孔相关联地具有第一骤冷空气入口孔和第二骤冷气孔，第一骤冷空气入口 骤冷气孔在第一横向方向上横向偏移，第二骤冷气孔沿与第一方向相反的第二横向方向横向偏移。

    Transition Nozzle Combustion System
    5.
    发明申请
    Transition Nozzle Combustion System 有权
    过渡喷嘴燃烧系统

    公开(公告)号：US20130255266A1

    公开(公告)日：2013-10-03

    申请号：US13437953

    申请日：2012-04-03

    申请人： Won-Wook Kim ,  Kevin Weston McMahan ,  Jaime Javier Maldonado

    发明人： Won-Wook Kim ,  Kevin Weston McMahan ,  Jaime Javier Maldonado

    IPC分类号： F23R3/02 ,  F23R3/04

    CPC分类号： F01D9/023 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

    摘要： The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

    摘要翻译： 本申请提供了一种用于冷却流的燃烧系统。 燃烧系统可以包括头端，后端，从头端延伸到后端的过渡喷嘴和围绕过渡喷嘴的冲击套筒。 冲击套筒可以限定与头端连通的用于冷却流的第一部分的第一空腔和与后端连通的用于冷却流的第二部分的第二空腔。 过渡喷嘴可以包括与冷却流的第二部分连通的多个冷却孔。

    GAS TURBINE COMBUSTOR WITH QUENCH WAKE CONTROL
    6.
    发明申请
    GAS TURBINE COMBUSTOR WITH QUENCH WAKE CONTROL 有权
    燃气涡轮机燃烧器，带有QUENCH WAKE控制

    公开(公告)号：US20110048024A1

    公开(公告)日：2011-03-03

    申请号：US12550845

    申请日：2009-08-31

    申请人： Timothy S. Snyder ,  Won-Wook Kim

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

    IPC分类号： F02C3/14

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

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

    摘要翻译： 燃气涡轮发动机具有燃烧器模块，该燃烧器模块包括环形燃烧器，该环形燃烧器具有限定环形燃烧室的衬套组件，并且包括周向排的多个相对较大的燃烧稀释空气进入孔和周向排的多个较小的骤冷空气入口 相对于燃烧气体产物的流动设置在下游的孔。 多个骤冷空气入口相对于设置在其上游的多个相对较大的稀释空气进入孔布置，使得与每个稀释空气入口孔相关联地具有第一骤冷空气入口孔和第二骤冷气孔，第一骤冷空气入口 骤冷气孔在第一横向方向上横向偏移，第二骤冷气孔沿与第一方向相反的第二横向方向横向偏移。

    Advanced quench pattern combustor
    7.
    发明授权
    Advanced quench pattern combustor 有权
    高级淬火图案燃烧器

    公开(公告)号：US08910481B2

    公开(公告)日：2014-12-16

    申请号：US12466948

    申请日：2009-05-15

    申请人： Won-Wook Kim ,  Timothy S. Snyder

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

    IPC分类号： F23R3/06

    CPC分类号： F23R3/06

    摘要： A combustor for a gas turbine engine is provided. The combustor includes a forward bulkhead, an inner radial combustor wall, and an outer radial combustor wall. The bulkhead includes a plurality of circumferentially disposed injector apertures. The inner radial combustor wall includes a plurality of inner quench aperture sets. Each inner quench aperture set includes a first inner quench aperture and a second inner quench aperture separated from each other by an inner interset distance. Each inner quench aperture set is separated from an adjacent inner quench aperture set by an inner intraset distance. The inner intraset distance is different than the inner interset distance. The outer radial combustor wall includes a plurality of circumferentially disposed outer quench apertures. The outer radial combustor wall is disposed radially outside of the inner radial combustor wall, thereby defining an annular combustion region therebetween.

    摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括前舱壁，内径向燃烧器壁和外径向燃烧室壁。 隔板包括多个周向设置的喷射孔。 内径向燃烧器壁包括多个内部淬火孔组。 每个内部骤冷孔径组件包括第一内部淬火孔和第二内部淬火孔，其彼此间隔内部距离。 每个内部淬火孔径组件与通过内部入座距离设置的相邻内部淬火孔径分离。 内部距离与内部距离不同。 外径向燃烧器壁包括多个周向设置的外部淬火孔。 外径向燃烧器壁设置在径向内径向燃烧室壁的外侧，从而在其间形成环形燃烧区域。

    Combustor with Non-Circular Head End
    8.
    发明申请
    Combustor with Non-Circular Head End 有权
    非圆形头端燃烧器

    公开(公告)号：US20130255262A1

    公开(公告)日：2013-10-03

    申请号：US13437954

    申请日：2012-04-03

    申请人： Won-Wook Kim ,  Kevin Weston McMahan

    发明人： Won-Wook Kim ,  Kevin Weston McMahan

    IPC分类号： F23R3/00 ,  F23R3/28

    CPC分类号： F01D9/023 ,  F05D2250/14 ,  F23C5/08 ,  F23R3/46 ,  F23R2900/00014

    摘要： The present application provides a combustor for use with a gas turbine engine. The combustor may include a head end with a non-circular configuration, a number of fuel nozzles positioned about the head end, and a transition piece extending downstream of the head end.

    摘要翻译： 本申请提供了一种与燃气涡轮发动机一起使用的燃烧器。 燃烧器可以包括具有非圆形构造的头端，围绕头端定位的多个燃料喷嘴，以及在头端下游延伸的过渡件。