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公开(公告)号：US08707707B2
公开(公告)日：2014-04-29
申请号：US12349744
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 is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto 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 supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译： 提供燃气涡轮发动机并且包括具有第一内部的燃烧器，其中供应到其中的第一燃料可燃，包括旋转的涡轮机叶片的涡轮机，至少可燃第一燃料的燃烧的产物可供给其中， 涡轮机叶片的过渡区域，包括第二内部，其中供应到其中的第二燃料和第一燃料的燃烧产物是可燃的，所述过渡区域设置成将燃烧器和涡轮机彼此流体地联接， 以及多个燃料喷射器，其由过渡区域支撑并且联接到燃料回路，并且构造成在单个轴向级，多个轴向级中的任何一个或多个中将第二燃料供应到第二内部， 单轴向圆周阶段和多个轴向周向阶段。
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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：US20100170251A1
公开(公告)日：2010-07-08
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，其中涡轮机，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：US20100170216A1
公开(公告)日：2010-07-08
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.
IPC分类号： F02C7/22
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：US20100170252A1
公开(公告)日：2010-07-08
申请号：US12349896
申请日：2009-01-07
IPC分类号： F02C1/00
CPC分类号： F02C7/22 , F02C3/20 , F23N1/002 , F23N2041/20 , F23R3/346 , F23R3/36 , Y02T50/677
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, 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燃烧器，其中第一燃料可燃，第一燃料包括天然气和/或天然气和由燃料回路从外部源接收的替代气体的混合物， 涡轮机，过渡区域，包括第二内部，其中第二燃料，第二燃料包括燃料回路可从外部源接收的替代气体的未混合供应，并且第一燃料的燃烧产物是可燃的， 以及多个燃料喷射器，其在结构上由过渡区域支撑并且联接到燃料回路，并且构造成在单个轴向级，多个轴向级中的任何一个中将第二燃料供应到第二内部，单个轴向级 轴向圆周阶段和多个轴向圆周阶段。
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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：US08701418B2
公开(公告)日：2014-04-22
申请号：US12349896
申请日：2009-01-07
CPC分类号： F02C7/22 , F02C3/20 , F23N1/002 , F23N2041/20 , F23R3/346 , F23R3/36 , Y02T50/677
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, 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燃烧器，其中第一燃料可燃，第一燃料包括天然气和/或天然气和由燃料回路从外部源接收的替代气体的混合物， 涡轮机，过渡区域，包括第二内部，其中第二燃料，第二燃料包括燃料回路可从外部源接收的替代气体的未混合供应，并且第一燃料的燃烧产物是可燃的， 以及多个燃料喷射器，其在结构上由过渡区域支撑并且联接到燃料回路，并且构造成在单个轴向级，多个轴向级中的任何一个中将第二燃料供应到第二内部，单个轴向级 轴向圆周阶段和多个轴向圆周阶段。
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公开(公告)号：US20100170254A1
公开(公告)日：2010-07-08
申请号：US12349744
申请日：2009-01-07
IPC分类号： F02C7/22
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto 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 supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译： 提供燃气涡轮发动机并且包括具有第一内部的燃烧器，其中供应到其中的第一燃料可燃，包括旋转的涡轮机叶片的涡轮机，至少可燃第一燃料的燃烧的产物可供给其中， 涡轮机叶片的过渡区域，包括第二内部，其中供应到其中的第二燃料和第一燃料的燃烧产物是可燃的，所述过渡区域设置成将燃烧器和涡轮机彼此流体地联接， 以及多个燃料喷射器，其由过渡区域支撑并且联接到燃料回路，并且构造成在单个轴向级，多个轴向级中的任何一个或多个中将第二燃料供应到第二内部， 单轴向圆周阶段和多个轴向周向阶段。
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公开(公告)号：US20130036743A1
公开(公告)日：2013-02-14
申请号：US13204777
申请日：2011-08-08
摘要： A combustor assembly includes a combustor body having a combustion chamber, and a nozzle support mounted to the combustor body. The nozzle support includes a central opening, and a plurality of openings extending about the central opening. A central flame tolerant nozzle assembly is positioned within the central opening, and a plurality of micro-mixer nozzle assemblies are mounted in respective ones of the plurality of openings about the central flame tolerant nozzle assembly. Each of the central flame tolerant nozzle assembly and the plurality of micro-mixer nozzle assemblies are configured and disposed to deliver an air-fuel mixture into the combustion chamber.
摘要翻译： 燃烧器组件包括具有燃烧室的燃烧器主体和安装到燃烧器主体的喷嘴支架。 喷嘴支撑件包括中心开口和围绕中心开口延伸的多个开口。 中心耐火喷嘴组件定位在中心开口内，并且多个微混合器喷嘴组件安装在围绕中心耐火喷嘴组件的多个开口中的相应开口中。 中央耐火喷嘴组件和多个微混合器喷嘴组件中的每一个被构造和布置成将空气 - 燃料混合物输送到燃烧室中。
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10.发明授权Method and arrangement for expanding a primary and secondary flame in a combustor 失效用于在燃烧器中膨胀一次和二次火焰的方法和装置公开(公告)号：US08156743B2
公开(公告)日：2012-04-17
申请号：US11418239
申请日：2006-05-04
IPC分类号： F02C1/00
CPC分类号： F23R3/16
摘要： Disclosed is an arrangement for expanding an annular fluid flow and a center fluid flow, comprising a combustor including a venturi and a centerbody, the centerbody including an upstream end and a downstream end, and a venturi throat defined by the venturi and disposed upstream of 0.19 inches downstream of the downstream end of the centerbody.
摘要翻译： 公开了一种用于扩展环形流体流和中心流体流的装置，其包括包括文丘里管和中心体的燃烧器，该中心体包括上游端和下游端，以及由文氏管限定的文丘里喉部并且设置在0.19 在中心体的下游端下游。
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