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1. 发明申请

US20100018210A1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US20100018210A1
公开(公告)日：2010-01-28
申请号：US12233903
申请日：2008-09-19
申请人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
发明人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.
摘要翻译：燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。

2. 发明授权

US08549859B2 Combustor apparatus in a gas turbine engine 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US08549859B2
公开(公告)日：2013-10-08
申请号：US12233903
申请日：2008-09-19
申请人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
发明人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
IPC分类号： F02C7/22
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.
摘要翻译：燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。

3. 发明授权

US09746185B2 Circumferential biasing and profiling of fuel injection in distribution ring 有权
公开(公告)号：US09746185B2
公开(公告)日：2017-08-29
申请号：US12712522
申请日：2010-02-25
申请人： David M. Ritland , Timothy A. Fox
发明人： David M. Ritland , Timothy A. Fox
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/286 , F02C7/22
摘要： An annular fluid distribution device (20) for distributing fluid into a gaseous flow (14), that includes: a first fluid distribution manifold (30) having a first fluid inlet and first fluid outlets (24), wherein the first fluid outlets inject a first fluid into the gaseous flow; and a second fluid distribution manifold (32), having a second fluid inlet and second fluid outlets (26), wherein the second fluid outlets inject a second fluid into the gaseous flow. The second fluid manifold is isolated from the first fluid distribution manifold, and the first fluid outlets and the second fluid outlets are disposed on a common fluid outlet plane (43).

4. 发明申请

US20120137691A1 Gas turbine assembly and method therefor 审中-公开
标题翻译：燃气轮机组件及其方法
公开(公告)号：US20120137691A1
公开(公告)日：2012-06-07
申请号：US12957476
申请日：2010-12-01
申请人： Andreas Bõttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
发明人： Andreas Bõttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
IPC分类号： F02C7/22 , B23P11/00
CPC分类号： F02C7/20 , F05D2260/94 , F05D2260/941 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00012 , Y10T29/49229
摘要： An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.
摘要翻译：提出了一种燃气轮机组件。组件包括通过燃气轮机的凸缘中的孔的气体供应管，用于将气体供应到燃气轮机的燃烧室，以及围绕气体供应管的套管，其具有第一端和第二端，其中第一端部密封地联接到气体供应管，并且其中套筒适于在第二端处密封地联接到凸缘，使得套筒沿着凸缘的厚度延伸。

5. 发明授权

US09488105B2 Gas turbine assembly and method therefor 有权
标题翻译：燃气轮机组件及其方法
公开(公告)号：US09488105B2
公开(公告)日：2016-11-08
申请号：US13885710
申请日：2011-11-30
申请人： Andreas Böttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
发明人： Andreas Böttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
IPC分类号： F02C7/22 , F23R3/28 , F02C7/20
CPC分类号： F02C7/20 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00012 , F23R2900/00017 , Y10T29/49229
摘要： An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.
摘要翻译：提出了一种燃气轮机组件。组件包括通过燃气轮机的凸缘中的孔的气体供应管，用于将气体供应到燃气轮机的燃烧室，以及围绕气体供应管的套管，其具有第一端和第二端，其中第一端部密封地联接到气体供应管，并且其中套筒适于在第二端处密封地联接到凸缘，使得套筒沿着凸缘的厚度延伸。

6. 发明申请

US20140130502A1 GAS TURBINE ASSEMBLY AND METHOD THEREFOR 有权
标题翻译：气体涡轮组件及其方法
公开(公告)号：US20140130502A1
公开(公告)日：2014-05-15
申请号：US13885710
申请日：2011-11-30
申请人： Andreas Böttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
发明人： Andreas Böttcher , Timothy A. Fox , Daniel W. Garan , Thomas Grieb , Jens Kleinfeld , Tobias Krieger , Stephen A. Ramier , David M. Ritland , Marcus Zurhorst
IPC分类号： F23R3/28 , F02C7/20
CPC分类号： F02C7/20 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00012 , F23R2900/00017 , Y10T29/49229
摘要： An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.
摘要翻译：提出了一种燃气轮机组件。组件包括通过燃气轮机的凸缘中的孔的气体供应管，用于将气体供应到燃气轮机的燃烧室，以及围绕气体供应管的套管，其具有第一端和第二端，其中第一端部密封地联接到气体供应管，并且其中套筒适于在第二端处密封地联接到凸缘，使得套筒沿着凸缘的厚度延伸。

7. 发明申请

US20110203284A1 CIRCUMFERENTIAL BIASING AND PROFILING OF FUEL INJECTION IN DISTRIBUTION RING 有权
标题翻译：燃油喷射在分配环中的循环偏心和分布
公开(公告)号：US20110203284A1
公开(公告)日：2011-08-25
申请号：US12712522
申请日：2010-02-25
申请人： David M. Ritland , Timothy A. Fox
发明人： David M. Ritland , Timothy A. Fox
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F02C7/22
摘要： An annular fluid distribution device (20) for distributing fluid into a gaseous flow (14), that includes: a first fluid distribution manifold (30) having a first fluid inlet and first fluid outlets (24), wherein the first fluid outlets inject a first fluid into the gaseous flow; and a second fluid distribution manifold (32), having a second fluid inlet and second fluid outlets (26), wherein the second fluid outlets inject a second fluid into the gaseous flow. The second fluid manifold is isolated from the first fluid distribution manifold, and the first fluid outlets and the second fluid outlets are disposed on a common fluid outlet plane (43).
摘要翻译：一种用于将流体分配到气流（14）中的环形流体分配装置（20），其包括：具有第一流体入口和第一流体出口（24）的第一流体分配歧管（30），其中第一流体出口注入第一流体进入气流; 和具有第二流体入口和第二流体出口（26）的第二流体分配歧管（32），其中所述第二流体出口将第二流体注入所述气体流中。第二流体歧管与第一流体分配歧管隔离，并且第一流体出口和第二流体出口设置在共同的流体出口平面（43）上。

8. 发明申请

US20100071377A1 Combustor Apparatus for Use in a Gas Turbine Engine 审中-公开
标题翻译：用于燃气轮机发动机的燃烧器装置
公开(公告)号：US20100071377A1
公开(公告)日：2010-03-25
申请号：US12477397
申请日：2009-06-03
申请人： Timothy A. Fox , David J. Wiebe
发明人： Timothy A. Fox , David J. Wiebe
IPC分类号： F02C7/22 , F02C5/02
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume.
摘要翻译：一种用于燃气涡轮发动机的燃烧器装置。燃烧器装置包括衬套，流动套筒和燃料喷射系统。内衬包括内部容积，其中内部容积的一部分限定主燃烧区。流动套筒容纳压缩空气，从衬套径向向外定位，并且包括前端和后端。燃料喷射系统联接到流动套筒并且将燃料提供到主燃烧区下游的衬套的内部容积中。燃料喷射系统包括燃料歧管和燃料分配结构。燃料歧管联接到流动套管并且包括用于接收燃料的空腔。燃料分配结构与空腔相关联，并将燃料从空腔分配到衬里内部容积。

9. 发明授权

US09016066B2 Combustor assembly in a gas turbine engine 有权
标题翻译：燃气轮机发动机中的燃烧器组件
公开(公告)号：US09016066B2
公开(公告)日：2015-04-28
申请号：US13718297
申请日：2012-12-18
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
IPC分类号： F23R3/60 , F23R3/04 , F23R3/28 , F23R3/00 , F23R3/34
CPC分类号： F23R3/286 , F23R3/002 , F23R3/34 , F23R3/346 , F23R3/60
摘要： A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.
摘要翻译：燃气涡轮发动机中的燃烧器组件包括燃烧器装置，燃料喷射系统，过渡管道和中间管道。燃烧器装置包括用于接收加压空气的流动套筒和由流动套筒包围的衬套。燃料喷射系统提供燃料以与加压空气混合并在衬套中点燃以产生燃烧产物。中间管道设置在衬套和过渡管道之间，以便限定燃烧产物从衬套流动到过渡管道的路径。中间管道与衬套相关联，使得其间可能发生运动，并且中间管道与过渡管道相关联，使得它们之间可能发生运动。流动套筒包括限定用于限制中间管道的轴向运动的轴向止动件的结构。

10. 发明授权

US08375726B2 Combustor assembly in a gas turbine engine 有权
标题翻译：燃气轮机发动机中的燃烧器组件
公开(公告)号：US08375726B2
公开(公告)日：2013-02-19
申请号：US12431302
申请日：2009-04-28
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
IPC分类号： F02C7/20 , F02C1/00 , F23R3/26
CPC分类号： F23R3/286 , F23R3/002 , F23R3/34 , F23R3/346 , F23R3/60
摘要： A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.
摘要翻译：燃气涡轮发动机中的燃烧器组件。燃烧器组件包括联接到主发动机壳体，第一燃料喷射系统，过渡管道和中间管道的燃烧器装置。燃烧器装置包括用于接收加压空气的流动套筒和从流动套管径向向内设置的衬套。第一燃料喷射系统提供燃料，其被加压空气点燃以产生第一工作气体。中间管道设置在衬套和过渡管道之间并且限定用于第一工作气体从衬套流动到过渡管道的路径。中间管道入口部分与衬套出口相关联并允许中间管道和衬套之间的移动。中间管道出口部分与过渡管道入口部分相关联并且允许中间管道和过渡管道之间的运动。

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