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公开(公告)号：US20110072826A1
公开(公告)日：2011-03-31
申请号：US12567534
申请日：2009-09-25
申请人： Venkateswarlu Narra , Lewis Berkley Davis, Jr. , Fei Han , Kwanwoo Kim , Kapil Kumar Singh , Shiva Kumar Srinivasan , Krishna Kumar Venkataraman
发明人： Venkateswarlu Narra , Lewis Berkley Davis, Jr. , Fei Han , Kwanwoo Kim , Kapil Kumar Singh , Shiva Kumar Srinivasan , Krishna Kumar Venkataraman
IPC分类号： F02C7/228
CPC分类号： F02C7/228 , F02C9/26 , F05D2270/14
摘要： In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor, the combustor cans being configured to receive compressed air from the compressor and to combust a fuel stream. The gas turbine system can also include a multi-circuit manifold coupled to the combustor cans and configured to provide a split fuel stream from the fuel stream to the combustor cans.
摘要翻译： 在示例性实施例中，提供燃气轮机系统。 燃气轮机系统可以包括被配置为压缩与压缩机流动连通的空气和燃烧器罐的压缩机，燃烧器罐被构造成从压缩机接收压缩空气并燃烧燃料流。 燃气轮机系统还可以包括耦合到燃烧器罐的多回路歧管并且构造成提供从燃料流到燃烧器罐的分离燃料流。
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公开(公告)号：US08408004B2
公开(公告)日：2013-04-02
申请号：US12485505
申请日：2009-06-16
申请人： Lewis Berkley Davis, Jr. , Fei Han , Shiva Srinivasan , Kapil Kumar Singh , Kwanwoo Kim , Venkateswarlu Narra
发明人： Lewis Berkley Davis, Jr. , Fei Han , Shiva Srinivasan , Kapil Kumar Singh , Kwanwoo Kim , Venkateswarlu Narra
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00013 , F23R2900/00014
摘要： A combustor for a gas turbine engine and related method is provided in which a plurality of combustor cans are selectively adapted with corresponding resonators. The resonators may, for example, be attached to every can in the consecutive arrangement of combustor cans, every other can, every third can or the like, and may be tuned to the same or first, second, third, etc. frequencies of operation. Such selective tuning is configured to suppress one or more of out-of-phase and in-phase dynamic interaction of streams discharged from adjacent combustor cans by changing the frequencies of pressure oscillation instabilities across the arrangement of consecutive cans.
摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器和相关方法，其中多个燃烧器罐选择性地适应于相应的谐振器。 例如，谐振器可以在燃烧器罐的连续布置中，每隔一个可以，每隔三分之一或者类似地连接到每个罐，并且可以调谐到相同或第一，第二，第三等操作频率 。 这种选择性调谐被配置为通过改变跨连续罐排列的压力振荡不稳定性的频率来抑制从相邻燃烧器罐排出的流的异相和同相动态相互作用中的一个或多个。
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公开(公告)号：US08683808B2
公开(公告)日：2014-04-01
申请号：US12349869
申请日：2009-01-07
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.
摘要翻译： 提供一种燃气涡轮发动机并且包括具有第一内部的燃烧器，其中由燃料回路供应到其中的第一燃料是可燃的，涡轮机，过渡区域，包括第二内部，其中燃料回路供应到其中的第二燃料 并且第一燃料的燃烧产物是可燃的，多个燃料喷射器在结构上由过渡区域支撑并且联接到燃料回路，并被构造成在任何一个中将第二燃料供应到第二内部 单个轴向级，多个轴向级，单个轴向圆周级和多个轴向圆周级的控制系统，以及耦合到燃料回路并被配置为控制由燃料回路供应到第一和第二燃料电路的第一和第二燃料的相对量 和第二内饰。
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公开(公告)号：US08457861B2
公开(公告)日：2013-06-04
申请号：US13594255
申请日：2012-08-24
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
摘要翻译： 提供了一种燃气涡轮发动机，并且包括具有第一内部的第一燃料可燃的燃烧器，至少可燃第一燃料的燃烧产物的涡轮机，包括第二内部的过渡区域，其中 第二燃料和第一燃料的燃烧产物是可燃的;多个燃料喷射器，其构造成在单个轴向级，多个轴向级，单个轴向周向级中的任一个中将第二燃料供应到第二内部 和多个轴向圆周级，压缩机，通过该压缩机将空气供应到第一和第二内部以用于其中的燃烧;以及控制系统，被配置为控制空气相对于第一和第二内部的相对量以及第一和第二内部的相对量 第二燃料供应到第一和第二内部。
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公开(公告)号：US08275533B2
公开(公告)日：2012-09-25
申请号：US13345362
申请日：2012-01-06
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
摘要翻译： 提供了一种燃气涡轮发动机，并且包括具有第一内部的第一燃料可燃的燃烧器，至少可燃第一燃料的燃烧产物的涡轮机，包括第二内部的过渡区域，其中 第二燃料和第一燃料的燃烧产物是可燃的;多个燃料喷射器，其构造成在单个轴向级，多个轴向级，单个轴向周向级中的任一个中将第二燃料供应到第二内部 和多个轴向圆周级，压缩机，通过该压缩机将空气供应到第一和第二内部以用于其中的燃烧;以及控制系统，被配置为控制空气相对于第一和第二内部的相对量以及第一和第二内部的相对量 第二燃料供应到第一和第二内部。
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公开(公告)号：US08701383B2
公开(公告)日：2014-04-22
申请号：US12349831
申请日：2009-01-07
申请人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, Jr.
发明人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, Jr.
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译： 提供了一种燃气涡轮发动机，并且包括具有第一内部的后倾稀注射（LLI）兼容的燃烧器，其中由燃料回路供应到其中的第一燃料可燃，涡轮机，过渡区域，其中第二内部 由燃料回路供应的燃料和第一燃料的燃烧产物是可燃的，过渡区设置成使燃烧器和涡轮彼此流体连接，并且多个燃料喷射器在结构上由 过渡区并且连接到燃料回路，并且其构造成在单个轴向级，多个轴向级，单个轴向圆周级和多个轴向圆周级中的任一个中将第二燃料供应到第二内部。
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公开(公告)号：US08112216B2
公开(公告)日：2012-02-07
申请号：US12349933
申请日：2009-01-07
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
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公开(公告)号：US08701382B2
公开(公告)日：2014-04-22
申请号：US12349791
申请日：2009-01-07
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Jason Charles Terry
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Jason Charles Terry
CPC分类号： F23R3/346 , F02C7/228 , F23C2900/07021 , F23N1/002 , F23N2025/08 , F23N2037/08 , F23N2041/20 , F23R3/286 , F23R3/36 , F23R3/40 , F23R2900/00002
摘要： A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译： 提供一种燃气涡轮发动机，包括燃料回路，燃料回路包括多个燃料回路分支，具有第一内部的燃烧器，其中多个燃料回路分支中的任何一个供给的第一燃料可燃，其中涡轮，过渡区， 包括第二内部，其中由多个燃料回路分支中的任何一个供应的第二燃料，包括燃料回路从外部源接收的气体的第二燃料和第一燃料的燃烧产物是可燃的， 过渡区域被设置成将燃烧器和涡轮机彼此流体耦合;以及多个燃料喷射器，其将第二燃料供应到单个轴向级，多个轴向级，单个轴向圆周段和 多个轴向周向阶段。
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公开(公告)号：US08019523B2
公开(公告)日：2011-09-13
申请号：US12349933
申请日：2009-01-07
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
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10.发明授权System and method of cooling turbine airfoils with sequestered carbon dioxide 失效用隔热二氧化碳冷却涡轮机翼的系统和方法公开(公告)号：US08631639B2
公开(公告)日：2014-01-21
申请号：US12413854
申请日：2009-03-30
IPC分类号： F02C7/16
摘要： A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a combustor, a turbine, a generator, and at least one shaft linking the compressor and turbine and generator together such that mechanical energy produced from the turbine is used to drive the compressor and the generator. Carbon dioxide that is sequestered from the exhaust of the turbine may be stored and injected back into the turbine to cool hot gas path components of the turbine.
摘要翻译： 具有由来自二氧化碳源的二氧化碳流提供的具有增强的冷却的涡轮发电系统以及使用二氧化碳流来冷却热气体路径部件的方法。 涡轮发电系统包括压缩机，燃烧器，涡轮机，发电机以及连接压缩机和涡轮机和发电机的至少一个轴，使得从涡轮机产生的机械能被用于驱动压缩机和发电机。 从涡轮机的排气隔离的二氧化碳可以被储存并注入到涡轮机中以冷却涡轮机的热气体路径部件。
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