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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：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：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：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：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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