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公开(公告)号：US20110041507A1
公开(公告)日：2011-02-24
申请号：US12543066
申请日：2009-08-18
Applicant: William Kirk Hessler , Jeffrey Lebegue , Predrag Popovic , Todd Daniel Paquin
Inventor： William Kirk Hessler , Jeffrey Lebegue , Predrag Popovic , Todd Daniel Paquin
IPC: F23R3/42
CPC classification number: F23R3/002 , F23R2900/00016
Abstract: A combustion liner assembly for a gas turbine combustor includes a plurality of fuel nozzles disposed circumferentially about a central axis of the combustor, and a venturi section disposed downstream of the fuel nozzles and connected to a head end of the liner assembly. The venturi section defines an annular throat area downstream of the fuel nozzles. A liner sleeve is connected to and commences at a downstream end of the venturi section. At least a portion of the venturi section serves as a liner upstream of the liner sleeve.
Abstract translation: 用于燃气轮机燃烧器的燃烧衬套组件包括围绕燃烧器的中心轴线周向设置的多个燃料喷嘴，以及设置在燃料喷嘴下游并连接到衬套组件的头端的文丘里管部分。 文丘里管部分限定在燃料喷嘴下游的环形喉部区域。 衬套套筒连接到文氏管部分的下游端并开始。 文氏管部分的至少一部分用作衬套上游的衬垫。
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公开(公告)号：US20100043441A1
公开(公告)日：2010-02-25
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
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。
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公开(公告)号：US20100018211A1
公开(公告)日：2010-01-28
申请号：US12219534
申请日：2008-07-23
Applicant: Krishna K. Venkataraman , William Kirk Hessler , Predrag Popovic
Inventor： Krishna K. Venkataraman , William Kirk Hessler , Predrag Popovic
CPC classification number: F01D9/023 , F05D2250/74 , F23R3/06
Abstract: A gas turbine transition piece includes a duct body having a forward end and an aft end, the duct body defining an enclosure for confining a flow of combustion products from a combustor to a turbine first stage nozzle. A plurality of dilution holes are formed in the duct body, located at selected X, Y, Z coordinates measured from a zero reference point at a center of an exit plane of the transition piece.
Abstract translation: 燃气涡轮机过渡件包括具有前端和后端的管道主体，管道主体限定用于限制来自燃烧器的燃烧产物流到涡轮机第一级喷嘴的外壳。 多个稀释孔形成在管体中，位于从过渡件的出口平面的中心处的零参考点测量的所选X，Y，Z坐标处。
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公开(公告)号：US20090019855A1
公开(公告)日：2009-01-22
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
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。
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25.发明申请Method and arrangement for expanding a primary and secondary flame in a combustor 失效用于在燃烧器中膨胀一次和二次火焰的方法和装置公开(公告)号：US20070256423A1
公开(公告)日：2007-11-08
申请号：US11418239
申请日：2006-05-04
Applicant: William Hessler , Alberto Negroni , Predrag Popovic , Krishna Venkataraman
Inventor： William Hessler , Alberto Negroni , Predrag Popovic , Krishna 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。
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Patent Agency Ranking
公开(公告)号：US20130098048A1
公开(公告)日：2013-04-25
申请号：US13278960
申请日：2011-10-21
Applicant: Predrag POPOVIC , Abinash BARUAH
Inventor： Predrag POPOVIC , Abinash BARUAH
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。
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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。
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28.发明申请APPARATUS AND METHOD FOR MINIMIZING AND/OR ELIMINATING DILUTION AIR LEAKAGE IN A COMBUSTION LINER ASSEMBLY 审中-公开用于最小化和/或消除燃烧衬套组件中的稀释空气泄漏的装置和方法公开(公告)号：US20110247340A1
公开(公告)日：2011-10-13
申请号：US12759042
申请日：2010-04-13
Applicant: Predrag POPOVIC , Krishna Kumar Venkataraman , Derrick Walter Simons , Ajay Kumar Gupta , William Kirk Hessler , Jeffrey Lebegue
Inventor： Predrag POPOVIC , Krishna Kumar Venkataraman , Derrick Walter Simons , Ajay Kumar Gupta , William Kirk Hessler , Jeffrey Lebegue
IPC: F23R3/42
CPC classification number: F23R3/02 , F23R3/002 , F23R2900/00001
Abstract: A combustion liner assembly for a gas turbine includes an outer liner, the outer liner having a flange at a forward end. An inner liner is disposed within the outer liner. The inner liner has a first inner wall. A venturi includes a second inner wall, a venturi throat, and the first inner wall of the inner liner. A slip joint is connected to the second inner wall. The slip joint receives the flange of the outer liner. Alternatively, or additionally, the combustion liner assembly includes a slip joint between the inner or outer liner and an aft section.
Abstract translation: 用于燃气轮机的燃烧衬套组件包括外衬套，外衬套在前端具有凸缘。 内衬被设置在外衬里内。 内衬具有第一内壁。 文氏管包括第二内壁，文丘里喉部和内衬的第一内壁。 滑动接头连接到第二内壁。 滑动接头容纳外衬套的凸缘。 替代地或另外地，燃烧衬套组件包括在内衬套或外衬套之间的滑动接头和后部段。
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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
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。
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30.发明授权Mixing hole arrangement and method for improving homogeneity of an air and fuel mixture in a combustor 有权混合孔布置和改进燃烧器中空气和燃料混合物均匀性的方法公开(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
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。
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