公开(公告)号：US09181876B2

公开(公告)日：2015-11-10

申请号：US13343286

申请日：2012-01-04

Applicant: Predrag Popovic ,  William Francis Carnell, Jr. ,  Andrew Mitchell Rodwell

Inventor： Predrag Popovic ,  William Francis Carnell, Jr. ,  Andrew Mitchell Rodwell

IPC: F02C7/16 ,  F02C6/08 ,  F02C7/224

CPC classification number: F02C7/16 ,  F02C6/08 ,  F02C7/143 ,  F02C7/224 ,  F05D2260/20

Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.

Abstract translation: 燃气轮机包括压缩机，压缩机下游的燃烧器和传热系统，其中传热系统从压缩机接收压缩的工作流体。 传热系统和燃烧器之间的流体耦合，其中流体联接器从传热系统接收压缩的工作流体。 与压缩机流体连通的调节器和传热系统和调节器之间的流体联接，其中流体联接器从热传递系统接收冷却介质。 用于操作燃气轮机的方法包括将压缩的工作流体从压缩机流动到传热系统，将热能从压缩的工作流体传递到传热系统，将压缩的工作流体从传热系统流到燃烧器， 并将冷却介质从传热系统流动到压缩机入口。

公开(公告)号：US08156743B2

公开(公告)日：2012-04-17

申请号：US11418239

申请日：2006-05-04

Applicant: William Kirk Hessler ,  Alberto Jose Negroni ,  Predrag Popovic ,  Krishna Kumar Venkataraman

Inventor： William Kirk Hessler ,  Alberto Jose Negroni ,  Predrag Popovic ,  Krishna Kumar Venkataraman

IPC: F02C1/00

CPC classification number: F23R3/16

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120036863A1

公开(公告)日：2012-02-16

申请号：US12856107

申请日：2010-08-13

Applicant: Joseph Kirzhner ,  Predrag Popovic ,  Roy Marshall Washam

Inventor： Joseph Kirzhner ,  Predrag Popovic ,  Roy Marshall Washam

IPC: F02C7/22 ,  F02C9/00

CPC classification number: F02C7/22 ,  F02C9/34 ,  F02C9/40

Abstract: In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for sustainable combustion during various stages of the turbine operation. In one aspect, combustible lean limit operation of the gas turbine free of lean blow out is enabled by adjusting fuel-air-ratio of the fuel and fuel-air mixture properties, based on the operation requirements of the turbine and flammability of the fuel components.

Abstract translation: 在操作燃气轮机时，在涡轮机运行的各个阶段期间燃料的期望的热值与用于可持续燃烧的燃料的实际需要之间可能存在差异。 在一个方面，通过基于涡轮机的操作要求和燃料组分的可燃性调节燃料和燃料 - 空气混合物性质的燃料空气比，能够实现无烟气的燃气轮机的可燃稀薄限制操作 。

公开(公告)号：US08096133B2

公开(公告)日：2012-01-17

申请号：US12153020

申请日：2008-05-13

Applicant: William K. Hessler ,  Predrag Popovic ,  Charles Nyberg

Inventor： William K. Hessler ,  Predrag Popovic ,  Charles Nyberg

IPC: F02C1/00 ,  F02G3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/26 ,  F23R2900/00012 ,  F23R2900/03042

Abstract: A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution air entry holes are formed in the cooling and dilution sleeve and a plurality of cooling and dilution air exit holes formed adjacent an aft edge of the liner such that, in use, cooling and dilution air flows through the cooling and dilution air entry holes, and through the plenum, exiting the cooling and dilution air exit holes, thereby cooling and dilution tuning the aft end of the combustor liner without having to remove the transition piece.

Abstract translation: 燃烧器衬套包括前端和后端，后端具有减小的直径部分，以及覆盖减小直径部分的冷却和稀释套筒，从而在它们之间建立冷却增压室。 在冷却和稀释套筒中形成多个冷却和稀释空气入口，以及在衬套的后边缘附近形成的多个冷却和稀释空气出口，使得在使用中冷却和稀释空气流过冷却和 稀释空气进入孔，并且通过增压室离开冷却和稀释空气出口，从而冷却和稀释调整燃烧器衬套的后端而不必去除过渡件。

公开(公告)号：US20100205970A1

公开(公告)日：2010-08-19

申请号：US12388855

申请日：2009-02-19

Applicant: William Kirk Hessler ,  Richard Gene Lowe ,  Predrag Popovic

Inventor： William Kirk Hessler ,  Richard Gene Lowe ,  Predrag Popovic

IPC: F02C7/22

CPC classification number: F23R3/343

Abstract: Provided are systems, methods, and apparatus providing secondary fuel nozzle assemblies. For example, a secondary fuel nozzle assembly can include a central portion having a proximal end and distal end, and defining a central passage therethrough, which can include at least one coiled tube extending through the central passage from the proximal end to the distal end; a flange having at least one main secondary fuel orifice in fluid communication with the central passage at the proximal end and at least one pilot orifice in fluid communication with the at least one coiled tube at the proximal end; and a tip portion having a proximal end and distal end, and defining at least one passage therethrough, which can be in fluid communication with the distal end of the at least one coiled tube and at least one orifice formed in the distal end of the tip portion.

Abstract translation: 提供了提供二次燃料喷嘴组件的系统，方法和装置。 例如，次级燃料喷嘴组件可以包括具有近端和远端的中心部分，并且限定穿过其中的中心通道，该中心通道可包括从近端延伸到远端延伸穿过中心通道的至少一个螺旋管; 具有至少一个主中间燃料孔口的凸缘，所述至少一个主次级燃料孔口在近端处与中心通道流体连通，以及至少一个引导孔口，其在近端与所述至少一个螺旋管道流体连通; 以及尖端部分，其具有近端和远端，并且限定穿过其中的至少一个通道，其可以与所述至少一个盘管的远端流体连通，并且形成在尖端的远端中的至少一个孔口 一部分。

公开(公告)号：US08955329B2

公开(公告)日：2015-02-17

申请号：US13278960

申请日：2011-10-21

Applicant: Predrag Popovic ,  Abinash Baruah

Inventor： Predrag Popovic ,  Abinash Baruah

IPC: F23R3/28 ,  F23D14/24

CPC classification number: F23D14/24 ,  F23R3/28

Abstract: A fuel nozzle assembly has been conceived for a combustor in a gas turbine including a first passage and fourth passage connectable to a source of gaseous fuel, a second passage connectable to a source of a gaseous oxidizer, and a third passage coupled to a source of a diluent gas, wherein the first passage is a center passage and is configured to discharge gaseous fuel from nozzles at a discharge end of the center passage, the second passage is configured to discharge the gaseous oxidizer through nozzles adjacent to the nozzles for the center passage, the third passage discharges a diluent gas through nozzles adjacent to the nozzles for the second passage, and the fourth passage is configured to discharges the gaseous fuel downstream of the discharge location for the first, second and third passages.

Abstract translation: 已经设计了一种用于燃气轮机中的燃烧器的燃料喷嘴组件，包括可连接到气态燃料源的第一通道和第四通道，可连接到气态氧化剂源的第二通道，以及连接到气体源的源的第三通道 稀释气体，其中第一通道是中心通道，并且构造成从中心通道的排放端处的喷嘴排出气体燃料，第二通道构造成通过与用于中心通道的喷嘴相邻的喷嘴排出气态氧化剂 第三通道通过与用于第二通道的喷嘴相邻的喷嘴排出稀释气体，并且第四通道被配置为排出第一，第二和第三通道的排放位置下游的气态燃料。

公开(公告)号：US20130167548A1

公开(公告)日：2013-07-04

申请号：US13343286

申请日：2012-01-04

Applicant: Predrag Popovic ,  William Francis Carnell, JR. ,  Andrew Mitchell Rodwell

Inventor： Predrag Popovic ,  William Francis Carnell, JR. ,  Andrew Mitchell Rodwell

IPC: F02C7/141

CPC classification number: F02C7/16 ,  F02C6/08 ,  F02C7/143 ,  F02C7/224 ,  F05D2260/20

Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.

Abstract translation: 燃气轮机包括压缩机，压缩机下游的燃烧器和传热系统，其中传热系统从压缩机接收压缩的工作流体。 传热系统和燃烧器之间的流体耦合，其中流体联接器从传热系统接收压缩的工作流体。 与压缩机流体连通的调节器和传热系统和调节器之间的流体联接，其中流体联接器从热传递系统接收冷却介质。 用于操作燃气轮机的方法包括将压缩的工作流体从压缩机流动到传热系统，将热能从压缩的工作流体传递到传热系统，将压缩的工作流体从传热系统流到燃烧器， 并将冷却介质从传热系统流动到压缩机入口。

公开(公告)号：US20120234011A1

公开(公告)日：2012-09-20

申请号：US13048564

申请日：2011-03-15

Applicant: Predrag Popovic ,  Abinash Baruah ,  Gilbert Otto Kraemer ,  William Thomas Ross

Inventor： Predrag Popovic ,  Abinash Baruah ,  Gilbert Otto Kraemer ,  William Thomas Ross

IPC: F02C7/22

CPC classification number: F23R3/28 ,  F23C2900/07022 ,  F23D14/22 ,  F23L7/00 ,  F23R3/10 ,  F23R3/283 ,  F23R3/343 ,  F23R3/346 ,  F23R3/46

Abstract: A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.

Abstract translation: 燃烧器包括具有喷嘴的端盖。 喷嘴具有前端面和中心轴线。 喷嘴包括多个燃料通道和多个氧化剂通道。 燃料通道构造成用于离开燃料通道的燃料。 燃料通道被定位成在第一方向上引导燃料，其中第一方向向内朝向中心轴线倾斜。 氧化剂通道构造成使氧化剂离开氧化剂通道。 氧化剂通道定位成在第二方向上引导氧化剂，其中第二方向与中心轴向外成一定角度。 多个燃料通道和多个氧化剂通道相对于彼此定位，使得燃料与氧化剂成交叉流动布置以在燃烧器中产生燃烧区域。

公开(公告)号：US20120102914A1

公开(公告)日：2012-05-03

申请号：US12938415

申请日：2010-11-03

Applicant: Joseph Kirzhner ,  Matthieu Paul Frederic Vierling ,  Nicolas Pourron ,  Denis Michel Martin ,  Predrag Popovic

Inventor： Joseph Kirzhner ,  Matthieu Paul Frederic Vierling ,  Nicolas Pourron ,  Denis Michel Martin ,  Predrag Popovic

IPC: F02C9/00 ,  G01M15/14

CPC classification number: F02C9/48 ,  F01D17/08 ,  F02C9/40 ,  F05D2260/80 ,  F05D2270/0831 ,  F05D2270/309

Abstract: Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

Abstract translation: 本发明的某些实施例可以包括用于补偿燃气轮机中的燃料组成变化的系统和方法。 根据本发明的示例性实施例，提供了一种用于补偿涡轮机中的燃料组成变化的方法。 该方法可以包括：监测与涡轮机燃烧器相关联的至少一个燃料参数; 监测与所述涡轮机燃烧器相关联的一个或多个燃烧动态特性; 监测与涡轮相关联的一个或多个性能和排放特性; 至少部分地基于所述至少一个燃料参数，所述一个或多个燃烧动态特性以及所述一个或多个性能和排放特征来估计燃料组成，并且至少部分地基于所估计的燃料来调整至少一个燃料参数 组成。

公开(公告)号：US20120023956A1

公开(公告)日：2012-02-02

申请号：US13217601

申请日：2011-08-25

Applicant: Predrag Popovic

Inventor： Predrag Popovic

IPC: F02C9/00 ,  F02C6/00

CPC classification number: F02C3/34 ,  F01K23/10 ,  F05D2260/61 ,  F25J3/04018 ,  F25J3/04127 ,  F25J3/04533 ,  F25J3/04569 ,  F25J3/046 ,  F25J2260/80

Abstract: A power plant and method of operation is provided. The power plant comprises at least one main air compressor, an oxidizer unit configured to deliver a compressed oxygen-rich gas flow to at least one gas turbine assembly. Each assembly comprises a turbine combustor for mixing the compressed oxygen-rich gas flow with a recirculated gas flow and a fuel stream to burn a combustible mixture and form the recirculated gas flow. The assembly also comprises a recirculation loop for recirculating the recirculated gas flow from a turbine to a turbine compressor. The assembly further comprises a recirculated gas flow extraction path for extracting a portion of the recirculated gas flow from the assembly and delivering this to a gas separation system. The gas separation system separates the portion of the recirculated gas flow into a nitrogen portion and a carbon dioxide portion.

Abstract translation: 提供电厂和操作方法。 发电厂包括至少一个主空气压缩机，氧化器单元，其被构造成将压缩的富氧气体流输送到至少一个燃气轮机组件。 每个组件包括涡轮机燃烧器，用于将经压缩的富氧气体流与再循环气体流和燃料流混合以燃烧可燃混合物并形成再循环气体流。 组件还包括用于将再循环的气体流从涡轮再循环到涡轮压缩机的再循环回路。 组件还包括再循环气流提取路径，用于从组件中提取一部分再循环气体流并将其输送到气体分离系统。 气体分离系统将再循环气体的一部分分离成氮气部分和二氧化碳部分。