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公开(公告)号：US20120198851A1
公开(公告)日：2012-08-09
申请号：US13449904
申请日：2012-04-18
申请人： Lewis Berkley Davis, JR. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
发明人： Lewis Berkley Davis, JR. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
IPC分类号： F23R3/28
摘要： A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention.
摘要翻译： 燃烧器包括中心燃料喷嘴组件和多个外部燃料喷嘴组件，所述多个外部燃料喷嘴组件中的每一个具有中心体和外部护罩，所述多个外部燃料喷嘴组件被配置为在 与中心圆筒的周围关系，使得在多个外部燃料喷嘴组件中的任何两个邻接的外部燃料喷嘴组件之间不存在间隙。 根据本发明的实施例，多个燃料喷嘴组件中的一个或多个可以轴向地前后移动。
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公开(公告)号：US08887507B2
公开(公告)日：2014-11-18
申请号：US13449904
申请日：2012-04-18
申请人： Lewis Berkley Davis, Jr. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
发明人： Lewis Berkley Davis, Jr. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
摘要： A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention.
摘要翻译： 燃烧器包括中心燃料喷嘴组件和多个外部燃料喷嘴组件，所述多个外部燃料喷嘴组件中的每一个具有中心体和外部护罩，所述多个外部燃料喷嘴组件被配置为在 与中心圆筒的周围关系，使得在多个外部燃料喷嘴组件中的任何两个邻接的外部燃料喷嘴组件之间不存在间隙。 根据本发明的实施例，多个燃料喷嘴组件中的一个或多个可以轴向地前后移动。
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公开(公告)号：US20100175380A1
公开(公告)日：2010-07-15
申请号：US12352674
申请日：2009-01-13
申请人： Lewis Berkley Davis, JR. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
发明人： Lewis Berkley Davis, JR. , Joseph Vincent Citeno , Thomas Edward Johnson , Willy Steve Ziminsky
摘要： A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention.
摘要翻译： 燃烧器包括中心燃料喷嘴组件和多个外部燃料喷嘴组件，所述多个外部燃料喷嘴组件中的每一个具有中心体和外部护罩，所述多个外部燃料喷嘴组件被配置为在 与中心圆筒的周围关系，使得在多个外部燃料喷嘴组件中的任何两个邻接的外部燃料喷嘴组件之间不存在间隙。 根据本发明的实施例，多个燃料喷嘴组件中的一个或多个可以轴向地前后移动。
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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：US20120312024A1
公开(公告)日：2012-12-13
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.
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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：US20100174466A1
公开(公告)日：2010-07-08
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
IPC分类号： F02C9/26
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：US20120110974A1
公开(公告)日：2012-05-10
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
IPC分类号： F23R3/28
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：US09822649B2
公开(公告)日：2017-11-21
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
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