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。

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

IPC分类号： F02C7/22 ,  F02C7/00 ,  F02C3/04

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。

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。

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

IPC分类号： F02C9/40 ,  F02C7/232

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.

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。

公开(公告)号：US20100170219A1

公开(公告)日：2010-07-08

申请号：US12349869

申请日：2009-01-07

申请人： Krishna Kumar Venkataraman ,  Lewis Berkley Davis, JR.

发明人： Krishna Kumar Venkataraman ,  Lewis Berkley Davis, JR.

IPC分类号： F02C9/28 ,  F02C7/22 ,  F02C9/40

CPC分类号： F23R3/346 ,  F02C7/228 ,  F02C9/28

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。

公开(公告)号：US20100326082A1

公开(公告)日：2010-12-30

申请号：US12494961

申请日：2009-06-30

申请人： Willy Steve Ziminsky ,  Lewis Berkley Davis, JR.

发明人： Willy Steve Ziminsky ,  Lewis Berkley Davis, JR.

IPC分类号： F02C1/00 ,  F02C7/22

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。

公开(公告)号：US20100247292A1

公开(公告)日：2010-09-30

申请号：US12413854

申请日：2009-03-30

申请人： Lewis Berkley Davis, JR. ,  Andres Garcia-Crespo, JR. ,  George M. Gilchrist, III ,  Amit S. Toprani

发明人： Lewis Berkley Davis, JR. ,  Andres Garcia-Crespo, JR. ,  George M. Gilchrist, III ,  Amit S. Toprani

IPC分类号： F01D13/02 ,  F01D5/08

CPC分类号： F01D25/12 ,  F01D5/081 ,  F02C1/08 ,  F02C3/34 ,  F02C6/18 ,  F02C7/18 ,  F05D2260/232

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。

公开(公告)号：US20100139280A1

公开(公告)日：2010-06-10

申请号：US12260451

申请日：2008-10-29

申请人： Benjamin Paul Lacy ,  Lewis Berkley Davis, JR. ,  Thomas Edward Johnson ,  William David York

发明人： Benjamin Paul Lacy ,  Lewis Berkley Davis, JR. ,  Thomas Edward Johnson ,  William David York

IPC分类号： F02C7/00 ,  B23P15/16

CPC分类号： F23R3/286 ,  F23D14/82 ,  F23D2900/00018 ,  Y10T29/49433

摘要： A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at least a portion of the fuel delivery plenum, each of the plurality of fuel mixing tubes including at least one fuel feed opening fluidly connected to the fuel delivery plenum; at least one thermal fuse disposed on an exterior surface of at least one tube, the at least one thermal fuse including a material that will melt upon ignition of fuel within the at least one tube and cause a diversion of fuel from the fuel feed opening to at least one bypass opening. A method and a turbine engine in accordance with the protection system are also provided.

摘要翻译： 一种用于涡轮发动机的预混合装置的保护系统，包括：主体，其具有共同建立燃料输送增压室的入口部分，出口部分和外壁; 以及多个燃料混合管，其延伸穿过所述燃料输送室的至少一部分，所述多个燃料混合管中的每一个包括流体连接到所述燃料输送室的至少一个燃料供给开口; 至少一个热熔丝设置在至少一个管的外表面上，所述至少一个热熔丝包括将在所述至少一个管内的燃料点燃时熔化的材料，并导致燃料从所述燃料供给口转向 至少一个旁路开口。 还提供了根据保护系统的方法和涡轮发动机。

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

IPC分类号： F23R3/42 ,  F02C7/22 ,  F02C3/14

CPC分类号： F01D9/023 ,  F01D9/041 ,  F23R3/002 ,  F23R3/286 ,  F23R3/46 ,  Y02T50/675

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。