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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：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：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：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：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：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：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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8.发明申请METHODS AND APPARATUS FOR COMBUSTOR FUEL CIRCUIT FOR ULTRA LOW CALORIFIC FUELS 有权用于超低温燃料的燃烧器燃料电路的方法和装置公开(公告)号：US20100326082A1
公开(公告)日：2010-12-30
申请号：US12494961
申请日：2009-06-30
CPC分类号： F23R3/28 , F23N2041/20 , F23R2900/00002
摘要： A method for controlling a gas turbine combustion system includes supplying an ultra low calorific fuel to a combustor of the combustion system through a first fuel circuit, controlling a supply of the ultra low calorific fuel through a second fuel circuit as required to control the volumetric flow of the ultra low calorific fuel through the combustor, and combusting the ultra low calorific fuel in the combustor.
摘要翻译： 一种用于控制燃气轮机燃烧系统的方法包括：通过第一燃料回路向燃烧系统的燃烧室供应超低热量燃料，根据需要控制通过第二燃料回路供应超低热量燃料以控制体积流量 的超低热量燃料，并且燃烧器内的超低热燃料燃烧。
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9.发明申请公开(公告)号：US20100115953A1
公开(公告)日：2010-05-13
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.
摘要翻译： 在燃气轮机中的一体式燃烧器和一级喷嘴包括燃烧室，其在分开的轴向位置处接收来自至少一个燃料喷嘴组的预混燃料和空气。 燃烧室包括将热燃烧气体输送到涡轮机的衬套和过渡件。 一级喷嘴，衬管和过渡件集成在一个单一部件中。 一个或多个燃料喷嘴组的至少一个轴向位置包括多个小型混合装置，其集中放热并减少火焰长度。
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公开(公告)号：US20100170219A1
公开(公告)日：2010-07-08
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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