公开(公告)号：US20120102967A1

公开(公告)日：2012-05-03

申请号：US12926121

申请日：2010-10-27

Applicant: Joseph Kirzhner ,  Predrag Popovic

Inventor： Joseph Kirzhner ,  Predrag Popovic

IPC: F02C9/00

CPC classification number: F23N5/242 ,  F23N2021/10 ,  F23N2021/12 ,  F23N2023/04 ,  F23N2023/08 ,  F23N2041/20 ,  F23R3/36 ,  F23R2900/00002 ,  Y02T50/677 ,  Y02T50/678

Abstract: A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.

Abstract translation: 用于防止或降低燃气轮机中燃烧不稳定性风险的方法和系统包括利用涡轮机控制器计算机处理器将包括特性变化率的预定和存储的稳定燃烧特性与实际操作燃烧特性进行比较。 如果实际的操作燃烧特性与稳定的燃烧特性不同，则控制器改变一个或多个最迅速地稳定燃气轮机的运行的燃气轮机操作参数。

公开(公告)号：US08028529B2

公开(公告)日：2011-10-04

申请号：US12219929

申请日：2008-07-30

Applicant: Krishna K. Venkataraman ,  William Kirk Hessler ,  Predrag Popovic

Inventor： Krishna K. Venkataraman ,  William Kirk Hessler ,  Predrag Popovic

IPC: F02C1/00

CPC classification number: F23R3/10 ,  F23D2900/00008 ,  F23R3/06 ,  F23R3/286 ,  F23R3/343

Abstract: A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece; a cap assembly attached to the primary combustion chamber, and an external turbulator member in operable communication with the cap assembly, wherein the primary combustion chamber includes a mixing hole arrangement for improving homogeneity of an air and fuel mixture in the combustor; the venturi throat is disposed within a predetermined distance upstream from the downstream end of the primary combustion chamber; the transition piece is composed of a duct body, with a plurality of dilution holes formed in the duct body; and the external turbulator member includes a step positioned at the second end of the centerbody, the step defining a radial distance about the second end of the centerbody.

Abstract translation: 一种燃气轮机燃烧器，包括：主燃烧室; 主燃烧室下游的二次燃烧室; 文丘里有文丘里喉咙; 过渡片 附接到所述主燃烧室的盖组件和与所述盖组件可操作地连通的外部湍流器构件，其中所述主燃烧室包括用于改善所述燃烧器中的空气和燃料混合物的均匀性的混合孔装置; 文丘里喉部设置在主燃烧室的下游端上游的预定距离内; 过渡件由管体构成，多个稀释孔形成在管体内; 并且所述外部紊流器构件包括位于所述中心体的第二端的台阶，所述台阶限定围绕所述中心体的第二端的径向距离。

公开(公告)号：US20100018181A1

公开(公告)日：2010-01-28

申请号：US12180879

申请日：2008-07-28

Applicant: Predrag Popovic ,  William Kirk Hessler ,  Krishna Kumar Venkataraman

Inventor： Predrag Popovic ,  William Kirk Hessler ,  Krishna Kumar Venkataraman

IPC: F02C7/042 ,  F02C9/00 ,  F02C7/14

CPC classification number: F23R3/005 ,  F23R3/045 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R3/42

Abstract: A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.

Abstract translation: 涡轮机包括燃烧器组件，附接到燃烧器组件的帽组件，帽组件内的中心体，中心体的壁，其具有第一端，第二端和中间部分，以及外部湍流构件，其可操作地与 盖组件。 外部紊流器构件与壁间隔开以形成由中心体的壁和外部湍流器之间的间隙限定的通道。 外部湍流器构件包括位于中心体的第二端的台阶。 该步骤限定了围绕中心体的第二端的径向距离。 外部紊流器构件形成为具有在约0.8至约1.2的范围内的相对于中心体的台阶间隙比。

公开(公告)号：US08397512B2

公开(公告)日：2013-03-19

申请号：US12197838

申请日：2008-08-25

Applicant: William Kirk Hessler ,  Predrag Popovic ,  Wei A. Chen ,  Tony Keith Davis

Inventor： William Kirk Hessler ,  Predrag Popovic ,  Wei A. Chen ,  Tony Keith Davis

IPC: F02C1/00

CPC classification number: F02C7/18 ,  F01D9/023 ,  Y10T29/49245

Abstract: A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.

Abstract translation: 一种用于组装燃气涡轮发动机的方法包括将过渡件联接在燃烧器衬套和喷嘴组件之间。 该方法还包括将过渡件的第一部分从燃烧器衬套的至少一部分延伸出来。 该方法还包括将流动套筒的第二部分联接到流动套筒的第一部分，使得流动套筒第二部分从流动套筒第一部分延伸并且至少部分地围绕过渡件的至少一部分延伸。 流动套筒第二部分包括与过渡件配合以至少部分地限定包括整体式勺状开口的整体冷却空气通道的勺子。 勺子被定向成将大致均匀的冷却空气流引入过渡件。

公开(公告)号：US08020385B2

公开(公告)日：2011-09-20

申请号：US12180879

申请日：2008-07-28

Applicant: Predrag Popovic ,  William Kirk Hessler ,  Krishna Kumar Venkataraman

Inventor： Predrag Popovic ,  William Kirk Hessler ,  Krishna Kumar Venkataraman

IPC: F02C1/00

CPC classification number: F23R3/005 ,  F23R3/045 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R3/42

Abstract: A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.

Abstract translation: 涡轮机包括燃烧器组件，附接到燃烧器组件的帽组件，帽组件内的中心体，中心体的壁，其具有第一端，第二端和中间部分，以及外部湍流构件，其可操作地与 盖组件。 外部紊流器构件与壁间隔开以形成由中心体的壁和外部湍流器之间的间隙限定的通道。 外部湍流器构件包括位于中心体的第二端的台阶。 该步骤限定了围绕中心体的第二端的径向距离。 外部紊流器构件形成为具有在约0.8至约1.2的范围内的相对于中心体的台阶间隙比。

公开(公告)号：US07887322B2

公开(公告)日：2011-02-15

申请号：US11531045

申请日：2006-09-12

Applicant: Predrag Popovic ,  Derrick Walter Simons ,  Krishna Kumar Venkataraman

Inventor： Predrag Popovic ,  Derrick Walter Simons ,  Krishna Kumar Venkataraman

IPC: F23D14/62 ,  F23C6/04

CPC classification number: F23R3/286 ,  F23R3/10

Abstract: Disclosed is a mixing hole arrangement for improving homogeneity of an air and fuel mixture in a combustor, the mixing hole arrangement comprising a plurality of mixing holes defined by a liner, wherein at least one of the plurality of mixing holes is a mixing hole that is at least one of sized and positioned to impede penetration of a fluid flow into a primary mixing zone located in a head end of the combustor.

Abstract translation: 公开了一种用于改善燃烧器中的空气和燃料混合物的均匀性的混合孔装置，该混合孔装置包括由衬套限定的多个混合孔，其中多个混合孔中的至少一个是混合孔， 至少一个尺寸和定位以阻止流体流入位于燃烧器头端的主混合区中。

公开(公告)号：US20090282833A1

公开(公告)日：2009-11-19

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

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：US20090260340A1

公开(公告)日：2009-10-22

申请号：US12104952

申请日：2008-04-17

Applicant: William Hessler ,  Predrag Popovic

Inventor： William Hessler ,  Predrag Popovic

IPC: F23R3/26 ,  F02C1/00 ,  B21D53/00

CPC classification number: F23R3/06 ,  F23R3/26 ,  F23R2900/00016 ,  Y10T29/49346

Abstract: A combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine are each provided. The combustor includes a combustion chamber along which a dilution breach is defined, a casing perimetrically surrounding the combustion chamber so as to define an airflow between the casing and the combustion chamber, the airflow being configured to supply dilution air to the combustion chamber via the dilution breach, and an easy to adjust dilution airflow tuning part disposed on the casing and in communication with the airflow. The dilution airflow tuning part is configured to increase and/or decrease an available amount of the dilution air to be supplied to the combustion chamber.

Abstract translation: 涡轮机的燃烧器，涡轮机的燃烧器的回装方法以及建立涡轮机的燃烧器的方法。 燃烧器包括燃烧室，沿着该燃烧室限定稀释破裂，围绕燃烧室的壳体，以便在壳体和燃烧室之间限定气流，气流被配置成经由稀释液向燃烧室供应稀释空气 以及易于调节的稀释气流调节部件，其设置在壳体上并与气流连通。 稀释气流调节部分被配置为增加和/或减少要供应到燃烧室的稀释空气的可用量。

公开(公告)号：US20080060358A1

公开(公告)日：2008-03-13

申请号：US11531045

申请日：2006-09-12

Applicant: Predrag Popovic ,  Derrick Walter Simons ,  Krishna Kumar Venkataraman

Inventor： Predrag Popovic ,  Derrick Walter Simons ,  Krishna Kumar Venkataraman

IPC: F02C1/00

CPC classification number: F23R3/286 ,  F23R3/10

Abstract: Disclosed is a mixing hole arrangement for improving homogeneity of an air and fuel mixture in a combustor, the mixing hole arrangement comprising a plurality of mixing holes defined by a liner, wherein at least one of the plurality of mixing holes is a mixing hole that is at least one of sized and positioned to impede penetration of a fluid flow into a primary mixing zone located in a head end of the combustor.

Abstract translation: 公开了一种用于改善燃烧器中的空气和燃料混合物的均匀性的混合孔装置，该混合孔装置包括由衬套限定的多个混合孔，其中多个混合孔中的至少一个是混合孔， 至少一个尺寸和定位以阻止流体流入位于燃烧器头端的主混合区中。

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。