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11.发明申请IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE 有权IMPINGEMENT SLEEVE AND METHODS FOR DESIGN AND FORMING IMPINGEMENT SLEEVE公开(公告)号：US20120304659A1
公开(公告)日：2012-12-06
申请号：US13589375
申请日：2012-08-20
申请人： Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
发明人： Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
CPC分类号： F01D9/023 , F05D2260/201 , F23R3/06 , F23R2900/03044
摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.
摘要翻译： 公开了一种冲击套筒和用于设计和形成冲击套筒的方法。 在一个实施例中，冲击套筒包括构造成至少部分地围绕燃烧器的过渡件的主体。 所述冲击套筒还包括限定在所述主体中的多个冷却孔，所述多个冷却孔具有冷却孔图案，所述冷却孔图案被配置为为所述过渡件提供期望的操作值。 多个冷却孔中的至少一个具有至少部分地在所述多个冷却孔中的至少一个冷却孔的入口和出口之间延伸的倒角。 多个冷却孔的至少一部分大体上是纵向不对称的。
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12.发明授权公开(公告)号：US08938978B2
公开(公告)日：2015-01-27
申请号：US13099938
申请日：2011-05-03
申请人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
发明人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
CPC分类号： F23R3/283 , F23D2900/00003 , F23R3/286 , F23R3/46 , F23R3/54 , F23R2900/00017 , F23R2900/00018
摘要： A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
摘要翻译： 提供了一种燃气涡轮发动机燃烧器，其包括燃料喷嘴阵列，围绕燃料喷嘴阵列设置的燃烧壳体组件和设置在燃烧壳体组件内的端盖组件，以便与燃烧壳体组件形成轴对称的环通过 所述流体行进到每个燃料喷嘴中，燃烧壳体组件和端盖组件中的至少一个形成有叶状的三维轮廓。
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13.发明授权Gas turbine combustor endcover assembly with integrated flow restrictor and manifold seal 有权具有集成流量限制器和歧管密封件的燃气轮机燃烧器整流器组件公开(公告)号：US08820086B2
公开(公告)日：2014-09-02
申请号：US13008399
申请日：2011-01-18
IPC分类号： F02C1/00
CPC分类号： F23R3/283 , F23K5/14 , F23K2900/05142 , F23R2900/00005 , F23R2900/00012
摘要： An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.
摘要翻译： 适于支撑一个或多个燃烧器喷嘴的用于涡轮机燃烧器的封盖组件包括基本平坦的板，其具有一个侧面，其在使用中面向燃烧室，在使用中相对侧面远离燃烧室。 至少一个燃料通道延伸穿过基本平坦的板。 燃料歧管移动块被固定到平板的相对侧，其中至少一个端口与至少一个通道对准。 形成有多个流动孔的燃料限制器插件位于平板和燃料歧管移动块之间，与至少一个燃料通道和至少一个端口对准。
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公开(公告)号：US08528839B2
公开(公告)日：2013-09-10
申请号：US13009108
申请日：2011-01-19
IPC分类号： F02C7/22
CPC分类号： B22D25/00 , F23C2900/07001 , F23D2900/00008 , F23R3/14 , F23R3/286 , F23R2900/00018 , Y02T50/675
摘要： A combustor nozzle includes a single-piece swirler. The single-piece swirler includes a center body extending axially along the single-piece swirler, a first fuel passage inside the center body, and a plurality of vanes extending radially from the center body. A method for fabricating a combustor nozzle includes casting a single-piece swirler having a center body and a plurality of vanes extending radially from the center body.
摘要翻译： 燃烧器喷嘴包括单件旋流器。 单件旋流器包括沿着单件旋流器轴向延伸的中心体，中心体内的第一燃料通道和从中心体径向延伸的多个叶片。 一种用于制造燃烧器喷嘴的方法包括浇铸具有中心体的单件旋流器和从中心体径向延伸的多个叶片。
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公开(公告)号：US20120180494A1
公开(公告)日：2012-07-19
申请号：US13006741
申请日：2011-01-14
IPC分类号： F02C7/22
CPC分类号： F23R3/283 , F23K5/007 , F23K2401/20 , F23R2900/00001 , F23R2900/00005
摘要： According to one aspect of the invention, a fuel nozzle assembly for a turbine includes an inner conduit and a flange coupled to the inner conduit thereby forming a chamber for flow of a gas fuel. In addition, the flange includes a diaphragm member coupled to the inner conduit, the diaphragm member being configured to flex in response to relative movement between the inner conduit and the flange.
摘要翻译： 根据本发明的一个方面，一种用于涡轮机的燃料喷嘴组件包括内部管道和联接到内部管道的凸缘，从而形成用于气体燃料流动的室。 此外，凸缘包括联接到内部管道的隔膜构件，隔膜构件被构造成响应于内部管道和法兰之间的相对运动而弯曲。
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公开(公告)号：US20120174589A1
公开(公告)日：2012-07-12
申请号：US12986611
申请日：2011-01-07
CPC分类号： F02C3/14 , F02C7/22 , F02C7/28 , F02C9/26 , F23R3/002 , F23R3/28 , F23R3/46 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
摘要： An end cover assembly is provided in combination with a gas turbine combustor for capping a back end of a combustion chamber. The end cover assembly includes an end cover plate securable to the back end of the combustion chamber, and a monolith block secured to the end cover plate. The end cover plate is constructed without welded gas passage plates and without brazed flow passage inserts and includes fuel channels therethrough, where the fuel channels are sized and positioned to interact with fuel nozzle inlet ports. The monolith block includes internal fuel gas passages positioned relative to the fuel channels in the end cover plate to commute fuel gas to the fuel channels of the end cover plate.
摘要翻译： 与燃气轮机燃烧器组合设置端盖组件，用于封盖燃烧室的后端。 端盖组件包括可固定到燃烧室的后端的端盖板和固定到端盖板的整体块。 端盖板构造成没有焊接气体通道板，没有钎焊流路插入件，并且包括通过其中的燃料通道，其中燃料通道的尺寸和位置与燃料喷嘴入口相互作用。 整体块包括相对于端盖板中的燃料通道定位的内部燃料气体通道，以将燃料气体换向端盖板的燃料通道。
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公开(公告)号：US20120274005A1
公开(公告)日：2012-11-01
申请号：US13094491
申请日：2011-04-26
CPC分类号： B22C9/043 , B29C64/00 , B33Y80/00 , Y02P10/292
摘要： A process for preparing for casting is provided and includes forming a cast component defining an interior having a complex and/or irregular shape, introducing a non-solid material into the cast component interior and solidifying the non-solid material to form an inner shell, forming an outer shell about the cast component and removing the cast component from between the inner and outer shells.
摘要翻译： 提供了一种用于铸造的制备方法，包括形成限定具有复合和/或不规则形状的内部的铸造组件，将非固体材料引入铸造组件内部并固化非固体材料以形成内壳， 围绕铸造部件形成外壳并从内壳和外壳之间移除铸造部件。
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公开(公告)号：US09341376B2
公开(公告)日：2016-05-17
申请号：US13400248
申请日：2012-02-20
摘要： A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.
摘要翻译： 燃烧器包括具有上游和下游表面的端盖和围绕上游表面和下游表面的盖罩。 第一组和第二组预混合管从上游表面延伸穿过下游表面。 第一燃料管道向第一组预混合器管供应燃料。 壳体周向地围绕盖罩以限定环形通道，并且第二燃料管道将燃料通过环形通道供应到第二组预混合器管。 用于向燃烧器供应燃料的方法包括使工作流体流过第一组和第二组预混合器管，将第一燃料流入第一组预混合器管，并使第二种燃料流过围绕端盖的环形通道并进入 第二组预混管。
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公开(公告)号：US09249678B2
公开(公告)日：2016-02-02
申请号：US13534744
申请日：2012-06-27
摘要： A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.
摘要翻译： 用于燃气涡轮机的燃烧器的过渡管道通常包括在过渡管道的后端具有框架的过渡管道。 框架通常包括下游端，径向外部，与径向外部相对的径向内部，径向外部和内部之间的第一侧部以及与第一侧部相对的第二侧部。 框架的第一侧部分中的槽可以具有与框架的下游端相邻的下游表面。 具有内表面，外表面和多个间隔件的隔热罩可以从隔热罩内表面大致向外延伸，使得内表面邻近槽下游表面和框架下游端。
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20.发明授权公开(公告)号：US09188342B2
公开(公告)日：2015-11-17
申请号：US13425950
申请日：2012-03-21
CPC分类号： F23R3/286 , F02C7/24 , F05D2260/963 , F23M20/005 , F23R3/32 , F23R2900/00014 , F23R2900/03044
摘要： Embodiments of the present application can provide systems and methods for dampening combustor dynamics. According to one embodiment, the system may include a micromixer. The system may also include at least one annular resonator disposed within the micromixer adjacent to a cap face plate or an impingement plate of the micromixer. The at least one annular resonator may include a first side including a number of holes forming a cold side hole pattern, a second side including a number of holes forming a hot side hole pattern, and a cavity substantially defined by the first side and the second side.
摘要翻译： 本申请的实施例可以提供用于衰减燃烧室动力学的系统和方法。 根据一个实施例，系统可以包括微混合器。 该系统还可以包括设置在微型混合器内的至少一个环形谐振器，其邻近盖板或微型混合器的冲击板。 所述至少一个环形谐振器可以包括包括形成冷侧孔图案的多个孔的第一侧，包括形成热侧孔图案的多个孔的第二侧和基本上由第一侧和第二侧形成的空腔 侧。
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