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公开(公告)号：US08826667B2
公开(公告)日：2014-09-09
申请号：US13115018
申请日：2011-05-24
申请人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
发明人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
CPC分类号： F23R3/002 , F23R3/045 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，在燃烧衬套和流动套筒之间的空气通道，以及在燃烧衬套和燃烧衬套之间延伸的结构 流动套管 该结构妨碍通过空气通道的气流路径。 燃气轮机燃烧器还包括空气动力尾流减速器，其被配置成重新定向结构周围的气流以减少结构下游的尾流区域。
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公开(公告)号：US08925326B2
公开(公告)日：2015-01-06
申请号：US13115009
申请日：2011-05-24
CPC分类号： F23R3/60 , F23D2900/14004 , F23R3/002 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，燃烧衬套和流动套筒之间的空气通道以及设置在空气通道中的空气动力学安装组件 。 空气动力学安装组件构造成将燃烧衬套保持在流动套筒内。 空气动力学安装组件包括联接到流动套管的流动套筒安装件和联接到燃烧衬套的衬套止动件。 流动套管安装件包括空气动力学形状的第一部分，并且衬套止动件包括空气动力学形状的第二部分，其被构造成将气流引导到空气动力学安装组件下游的尾流区域。 流动套筒安装件和衬套止动件彼此联接以限定空气动力学形状。
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公开(公告)号：US20120297783A1
公开(公告)日：2012-11-29
申请号：US13115018
申请日：2011-05-24
申请人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
发明人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
CPC分类号： F23R3/002 , F23R3/045 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，在燃烧衬套和流动套筒之间的空气通道，以及在燃烧衬套和燃烧衬套之间延伸的结构 流动套管 该结构妨碍通过空气通道的气流路径。 燃气轮机燃烧器还包括空气动力尾流减速器，其被配置成重新定向结构周围的气流以减少结构下游的尾流区域。
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公开(公告)号：US20120297782A1
公开(公告)日：2012-11-29
申请号：US13115009
申请日：2011-05-24
CPC分类号： F23R3/60 , F23D2900/14004 , F23R3/002 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，燃烧衬套和流动套筒之间的空气通道以及设置在空气通道中的空气动力学安装组件 。 空气动力学安装组件构造成将燃烧衬套保持在流动套筒内。 空气动力学安装组件包括联接到流动套管的流动套筒安装件和联接到燃烧衬套的衬套止动件。 流动套管安装件包括空气动力学形状的第一部分，并且衬套止动件包括空气动力学形状的第二部分，其被构造成将气流引导到空气动力学安装组件下游的尾流区域。 流动套筒安装件和衬套止动件彼此联接以限定空气动力学形状。
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公开(公告)号：US20120297784A1
公开(公告)日：2012-11-29
申请号：US13115051
申请日：2011-05-24
IPC分类号： F23R3/16
CPC分类号： F23R3/002 , F23R3/48 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，燃烧衬套和流动套筒之间的空气通道以及设置在空气通道中的气流引导叶片 。 气流引导叶片包括上游叶片部分和下游叶片部分。 上游叶片部分与燃气轮机燃烧器的轴线成一角度定向。 下游叶片部分与轴向对准。 气流引导叶片被构造成去除气流引导叶片上游的气流的周向漩涡，以沿着轴向平衡气流引导叶片下游的气流。
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公开(公告)号：US20120308947A1
公开(公告)日：2012-12-06
申请号：US13154027
申请日：2011-06-06
CPC分类号： F23R3/002 , F23R3/04 , F23R3/10 , F23R3/286 , F23R2900/03044 , Y10T29/49348
摘要： A combustor having a pressure feed is provided and includes an outer vessel, an intermediate vessel disposed within the outer vessel to form an outer annulus, an inner vessel disposed within the intermediate vessel to form an inner annulus between the intermediate and inner vessels, by which upstream portions of fuel nozzles disposed within the inner vessel are fed, and an internal volume within the inner vessel about downstream portions of the fuel nozzles and a tubular assembly by which the outer annulus and the internal volume are communicative.
摘要翻译： 提供了具有压力进料的燃烧器，并且包括外部容器，设置在外部容器内以形成外部环空的中间容器，设置在中间容器内的内部容器，以在中间容器和内部容器之间形成内部环空， 供给设置在内部容器内的燃料喷嘴的上游部分，以及内部容器内的内部容积，其内部容器围绕燃料喷嘴的下游部分和管状组件，外部环空和内部容积通过该管状组件连通。
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公开(公告)号：US09068750B2
公开(公告)日：2015-06-30
申请号：US13040289
申请日：2011-03-04
摘要： The present application and the resulting patent provide a pre-nozzle mixing cap assembly positioned about a cap member of a combustor for mixing a flow of air and a flow of fuel. The pre-nozzle mixing cap assembly may include a fuel plenum in communication with the flow of fuel and a number of tubes in communication with the flow of air and extending through the fuel plenum. Each of the tubes may include a number of fuel holes therein such that the flow of fuel in the fuel plenum passes through the fuel holes and mixes with the flow of air.
摘要翻译： 本申请和所得专利提供了一种预喷嘴混合盖组件，其围绕燃烧器的盖构件定位，以混合空气流和燃料流。 预喷嘴混合盖组件可以包括与燃料流连通的燃料增压室和与空气流连通并延伸通过燃料增压室的多个管。 每个管可以在其中包括多个燃料孔，使得燃料气室中的燃料流通过燃料孔并与空气流混合。
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公开(公告)号：US20140020389A1
公开(公告)日：2014-01-23
申请号：US13555481
申请日：2012-07-23
IPC分类号： F23R3/46
CPC分类号： F23R3/10 , F23R3/283 , F23R3/46 , F23R2900/03042 , F23R2900/03044
摘要： One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要翻译： 本发明的一个实施例是用于燃烧器燃料喷嘴盖组件的盖插件。 盖插件通常包括限定燃料喷嘴通道并且可具有上游周边边缘的盖板。 具有主体的冲击板可以大致限定轴向延伸的环形套筒和周向围绕主体的径向外部部分。 径向外部可包括与下游端轴向分离的上游端。 轴向延伸的环形套筒可以限定通过本体的环形通道。 盖板上游周边边缘可以与冲击板主体径向外部的下游端相邻。
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公开(公告)号：US20120279224A1
公开(公告)日：2012-11-08
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
IPC分类号： F23C3/00
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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公开(公告)号：US09175857B2
公开(公告)日：2015-11-03
申请号：US13555481
申请日：2012-07-23
CPC分类号： F23R3/10 , F23R3/283 , F23R3/46 , F23R2900/03042 , F23R2900/03044
摘要： One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要翻译： 本发明的一个实施例是用于燃烧器燃料喷嘴盖组件的盖插件。 盖插件通常包括限定燃料喷嘴通道并且可具有上游周边边缘的盖板。 具有主体的冲击板可以大致限定轴向延伸的环形套筒和周向围绕主体的径向外部部分。 径向外部可包括与下游端轴向分离的上游端。 轴向延伸的环形套筒可以限定通过本体的环形通道。 盖板上游周边边缘可以与冲击板主体径向外部的下游端相邻。
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