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。

公开(公告)号：US20130025293A1

公开(公告)日：2013-01-31

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： F02C1/06 ,  F23R3/20 ,  F23R3/06

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。

公开(公告)号：US20100287941A1

公开(公告)日：2010-11-18

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： F02C1/00

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。

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。

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。

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。

公开(公告)号：US20130283802A1

公开(公告)日：2013-10-31

申请号：US13457754

申请日：2012-04-27

申请人： Won-Wook Kim ,  Jeffrey Scott LeBegue ,  Kevin Weston McMahan

发明人： Won-Wook Kim ,  Jeffrey Scott LeBegue ,  Kevin Weston McMahan

IPC分类号： F23R3/42 ,  F01D9/02 ,  F23R3/28 ,  F23R3/10

CPC分类号： F23R3/286 ,  F23R3/425 ,  F23R3/46

摘要： A combustor includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface. A shroud circumferentially surrounds at least a portion of the end cap, wherein the shroud at least partially defines a fuel plenum between the upstream surface and the downstream surface. A combustion chamber downstream from the end cap defines a longitudinal axis. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap to the combustion chamber. A transition duct circumferentially surrounds at least a portion of the combustion chamber downstream from the end cap and curves tangentially from the longitudinal axis.

摘要翻译： 燃烧器包括径向延伸穿过燃烧器的至少一部分的端盖，其中端盖包括与下游表面轴向分离的上游表面。 护罩周向地围绕端盖的至少一部分，其中护罩至少部分地限定在上游表面和下游表面之间的燃料增压室。 在端盖下游的燃烧室限定纵向轴线。 多个管从上游表面延伸通过端盖的下游表面，以提供通过端盖到燃烧室的流体连通。 过渡管周向地围绕端盖下游的燃烧室的至少一部分并且与纵向轴线相切地弯曲。

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。

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。

公开(公告)号：US20130283804A1

公开(公告)日：2013-10-31

申请号：US13459516

申请日：2012-04-30

申请人： Jeffrey Scott LeBegue ,  Ronnie Ray Pentecost ,  James Scott Flanagan ,  Won-Wook Kim ,  Kevin Weston McMahan

发明人： Jeffrey Scott LeBegue ,  Ronnie Ray Pentecost ,  James Scott Flanagan ,  Won-Wook Kim ,  Kevin Weston McMahan

IPC分类号： F02C7/232

CPC分类号： F01D9/023 ,  F23R3/06 ,  F23R3/286 ,  F23R3/346 ,  F23R3/46 ,  F23R2900/03044

摘要： A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.

摘要翻译： 公开了一种用于向燃烧器供应喷射流体的系统。 该系统包括过渡管道，其包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 通道限定燃烧室。 该系统还包括提供流体连通的管，用于使注射流体流过过渡管并进入燃烧室。