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公开(公告)号：US08677759B2
公开(公告)日：2014-03-25
申请号：US12349173
申请日：2009-01-06
Applicant: Karthick Kaleeswaran , Rao Ganesh Pejawar , Sonal Bhojani
Inventor： Karthick Kaleeswaran , Rao Ganesh Pejawar , Sonal Bhojani
CPC classification number: F23R3/04 , F23R3/005 , F23R3/06 , F23R2900/03044
Abstract: A gas turbine combustor includes a liner having a forward end and an aft end; a flow sleeve surrounding the liner, the flow sleeve also having forward and aft ends, the aft end of the flow sleeve supporting an annular ring formed with a plurality of cooling bores and extending through the flow sleeve, at least some of the plurality of cooling bores formed at an acute angle relative to a longitudinal axis of the liner.
Abstract translation: 燃气轮机燃烧器包括具有前端和后端的衬套; 围绕所述衬套的流动套筒，所述流动套筒还具有前端和后端，所述流动套筒的后端支撑形成有多个冷却孔并延伸穿过所述流动套筒的环形环，所述多个冷却中的至少一些冷却 相对于衬套的纵向轴线成锐角形成的孔。
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公开(公告)号：US08528338B2
公开(公告)日：2013-09-10
申请号：US12960782
申请日：2010-12-06
Applicant: Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Inventor： Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Abstract: A method is provided for operating an air-staged diffusion nozzle for a gas turbine combustor to cool the nozzle tip and improve mixing of gas fuel and air within a downstream burner space. Air is mixed with the gas-fuel in an outer swirler and expanded in a downstream burner tube space. Compressed air from a cooling air cavity in the nozzle flows through an inner swirler, passing downstream from the tip of the nozzle to the burner tube space, cooling the nozzle tip and improving the mixing of the gas-fuel with air, thereby reducing emissions from the gas turbine and reducing soot formation in startup. Direction and rotation of the discharged air from the nozzle tip into the burner space may be arranged to promote nozzle tip cooling and gas-fuel mixing with air.
Abstract translation: 提供了一种用于操作用于燃气轮机燃烧器的空气扩散喷嘴以冷却喷嘴尖端并改善气体燃料和下游燃烧器空间内的空气的混合的方法。 空气与外旋流器中的气体燃料混合并在下游燃烧器管空间中膨胀。 来自喷嘴中的冷却空气腔的压缩空气流过内旋流器，从喷嘴尖端下游到燃烧器管空间，冷却喷嘴尖端，改善气体燃料与空气的混合，从而减少 燃气轮机和启动时减少烟灰形成。 排出的空气从喷嘴尖端到燃烧器空间的方向和旋转可以被布置成促进喷嘴尖端冷却和气体与空气的混合。
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公开(公告)号：US20130074507A1
公开(公告)日：2013-03-28
申请号：US13247008
申请日：2011-09-28
Applicant: Karthick KALEESWARAN , Sridhar K. V
Inventor： Karthick KALEESWARAN , Sridhar K. V
CPC classification number: F23R3/06 , F23R3/002 , Y10T29/49229
Abstract: A combustion liner for a combustor of a turbine engine includes a plurality of undulations which extend around the exterior circumference of the combustion liner. A plurality of rows of cooling holes are formed through the combustion liner. Each row of cooling holes is located in one of the undulations which extends around the exterior circumference of the combustion liner. The cooling holes admit a flow of cooling air into the interior of the combustion liner. The cooling holes are located and oriented to help the flow of cooling air form a film along the inner surface of the combustion liner.
Abstract translation: 用于涡轮发动机的燃烧器的燃烧衬套包括围绕燃烧衬套的外周延伸的多个起伏。 通过燃烧衬套形成多排冷却孔。 每排冷却孔位于沿着燃烧衬套外周延伸的一个起伏部分中。 冷却孔允许冷却空气流入燃烧衬套的内部。 冷却孔被定位和定向以帮助冷却空气的流动沿着燃烧衬套的内表面形成膜。
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公开(公告)号：US07757492B2
公开(公告)日：2010-07-20
申请号：US11750500
申请日：2007-05-18
Applicant: John Charles Intile , Madhavan Poyyapakkam , Ganesh Pejawar Rao , Karthick Kaleeswaran
CPC classification number: F01D9/023 , F05D2260/2212
Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.
Abstract translation: 一种方法有利于组装包括燃烧器组件和喷嘴组件的燃气涡轮发动机。 该方法包括提供包括第一端，第二端和在其间延伸的主体的过渡件，其中主体包括内表面，相对的外表面，将过渡件的第一端连接到燃烧器组件，以及联接 过渡件的第二端到喷嘴组件，使得在过渡件的外表面上螺旋延伸的湍流器从过渡件第一端延伸到过渡件第二端，以便于引起湍流以供应到燃烧器组件的冷却空气 。
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公开(公告)号：US20100170256A1
公开(公告)日：2010-07-08
申请号：US12349173
申请日：2009-01-06
Applicant: Karthick Kaleeswaran , Rao Ganesh Pejawar , Sonal Bhojani
Inventor： Karthick Kaleeswaran , Rao Ganesh Pejawar , Sonal Bhojani
IPC: F23R3/04
CPC classification number: F23R3/04 , F23R3/005 , F23R3/06 , F23R2900/03044
Abstract: A gas turbine combustor includes a liner having a forward end and an aft end; a flow sleeve surrounding the liner, the flow sleeve also having forward and aft ends, the aft end of the flow sleeve supporting an annular ring formed with a plurality of cooling bores and extending through the flow sleeve, at least some of the plurality of cooling bores formed at an acute angle relative to a longitudinal axis of the liner.
Abstract translation: 燃气轮机燃烧器包括具有前端和后端的衬套; 围绕所述衬套的流动套筒，所述流动套筒还具有前端和后端，所述流动套筒的后端支撑形成有多个冷却孔并延伸穿过所述流动套筒的环形环，所述多个冷却中的至少一些冷却 相对于衬套的纵向轴线成锐角形成的孔。
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Patent Agency Ranking
公开(公告)号：US20130232977A1
公开(公告)日：2013-09-12
申请号：US13415145
申请日：2012-03-08
Applicant: Prabhu Kumar Ippadi Siddagangaiah , Karthick Kaleeswaran
CPC classification number: F23R3/286 , F23R3/14 , F23R2900/00001 , F23R2900/00012
Abstract: A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart swirl to a working fluid flowing through the passages. A shroud including an upstream end axially separated from a downstream end surrounds the disk and extends downstream from the disk.
Abstract translation: 一种用于燃气轮机的燃料喷嘴包括环形通道，该环形通道构造成使燃料和与所述环形通道的第二端同轴并设置在其中的盘流动。 盘从第二端径向向外延伸。 多个通道延伸穿过盘并且构造成使流动通过通道的工作流体产生涡流。 包括从下游端轴向分离的上游端的护罩围绕盘并且从盘的下游延伸。
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公开(公告)号：US08429919B2
公开(公告)日：2013-04-30
申请号：US12473312
申请日：2009-05-28
Applicant: Karthick Kaleeswaran , Ganesh Pejawar Rao
Inventor： Karthick Kaleeswaran , Ganesh Pejawar Rao
CPC classification number: F16J15/0887 , F01D9/023 , F02C7/28 , F23R2900/00012
Abstract: The present invention provides a hula seal for use with a combustor. The hula seal includes a number of legs that define a number of slots. The slots may include a number of expansion slots.
Abstract translation: 本发明提供了一种与燃烧器一起使用的呼啦密封。 呼啦密封包括一些限定多个插槽的腿。 插槽可以包括多个扩展槽。
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公开(公告)号：US20120137703A1
公开(公告)日：2012-06-07
申请号：US12960782
申请日：2010-12-06
Applicant: Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Inventor： Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Abstract: A method is provided for operating an air-staged diffusion nozzle for a gas turbine combustor to cool the nozzle tip and improve mixing of gas fuel and air within a downstream burner space. Air is mixed with the gas-fuel in an outer swirler and expanded in a downstream burner tube space. Compressed air from a cooling air cavity in the nozzle flows through an inner swirler, passing downstream from the tip of the nozzle to the burner tube space, cooling the nozzle tip and improving the mixing of the gas-fuel with air, thereby reducing emissions from the gas turbine and reducing soot formation in startup. Direction and rotation of the discharged air from the nozzle tip into the burner space may be arranged to promote nozzle tip cooling and gas-fuel mixing with air.
Abstract translation: 提供了一种用于操作用于燃气轮机燃烧器的空气扩散喷嘴以冷却喷嘴尖端并改善气体燃料和下游燃烧器空间内的空气的混合的方法。 空气与外旋流器中的气体燃料混合并在下游燃烧器管空间中膨胀。 来自喷嘴中的冷却空气腔的压缩空气流过内旋流器，从喷嘴尖端下游到燃烧器管空间，冷却喷嘴尖端，改善气体燃料与空气的混合，从而减少 燃气轮机和启动时减少烟灰形成。 排出的空气从喷嘴尖端到燃烧器空间的方向和旋转可以被布置成促进喷嘴尖端冷却和气体与空气的混合。
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9.发明申请公开(公告)号：US20120048971A1
公开(公告)日：2012-03-01
申请号：US12871171
申请日：2010-08-30
Applicant: Karthick KALEESWARAN , Nitin SARJA , A. M. SATISH
Inventor： Karthick KALEESWARAN , Nitin SARJA , A. M. SATISH
IPC: B05B1/00
Abstract: One exemplary embodiment of a fuel nozzle flange includes an elongated flange body including a radial mounting flange at an aft end thereof and a face surface at a forward end thereof. The flange body has a first, axially-oriented through-bore adapted to receive a first fuel supply pipe at the forward end; a second, radially-oriented bore intersecting the first axially-oriented bore and adapted to receive a second fuel supply pipe; and a third axially-oriented through-bore adapted to receive one end of a flame detector device at the forward end.
Abstract translation: 燃料喷嘴凸缘的一个示例性实施例包括细长的凸缘体，其包括在其后端处的径向安装凸缘和其前端处的面表面。 凸缘体具有第一轴向定向的通孔，其适于在前端处接收第一燃料供应管; 第二径向定向的孔，与第一轴向定向的孔相交并且适于接收第二燃料供应管; 以及第三轴向定向的通孔，其适于在前端接收火焰检测器装置的一端。
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10.发明授权Fully impingement cooled venturi with inbuilt resonator for reduced dynamics and better heat transfer capabilities 有权具有内置谐振器的完全冲击冷却文丘里管，以减少动力学和更好的传热能力公开(公告)号：US08931280B2
公开(公告)日：2015-01-13
申请号：US13094160
申请日：2011-04-26
Applicant: Karthick Kaleeswaran , Kodukulla Venkat Sridhar , James Butts , Bhaskara Rao Atchuta , Prabhu Kumar Ippadi Siddagangaiah
Inventor： Karthick Kaleeswaran , Kodukulla Venkat Sridhar , James Butts , Bhaskara Rao Atchuta , Prabhu Kumar Ippadi Siddagangaiah
CPC classification number: F23R3/002 , F23R2900/03044
Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.
Abstract translation: 用于涡轮机燃烧器的文丘里组件包括基本上同心的关系彼此径向间隔开的第一外环形壁和第二中间环形壁。 第一外环形壁和所述第二中间环形壁成形为限定向前，基本上为V形的喉部区域和后部轴向延伸部分。 第三径向最内的环形壁在所述喉部区域的后端连接到第二中间环形壁。 第一多个孔被设置在大致V形的喉部区域中的第一外环形壁中，并且第二多个孔设置在所述第二中间环形壁的后部轴向延伸部分中，使得冷却空气流过 第一和第二多个孔以冲击冷却第三径向最内环形壁。
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