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公开(公告)号：US20140072401A1
公开(公告)日：2014-03-13
申请号：US13611223
申请日：2012-09-12
IPC: F01D1/04
CPC classification number: F01D9/04 , F05D2270/172
Abstract: An axial diffuser for a gas turbine includes diffuser walls that define diffuser channels receiving compressor discharge air. The diffuser walls diverge in a flow direction. A flow control device is disposed in the diffuser channels and includes a plasma controller that serves to ionize airflow in the diffuser channels.
Abstract translation: 用于燃气轮机的轴向扩散器包括限定扩散器通道的扩散壁，其接收压缩机排出空气。 扩散壁在流动方向上发散。 流量控制装置设置在扩散器通道中，并且包括用于电离扩散器通道中的气流的等离子体控制器。
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公开(公告)号：US08522556B2
公开(公告)日：2013-09-03
申请号：US12960767
申请日：2010-12-06
Applicant: Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Inventor： Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Abstract: In an air-staged diffusion nozzle for a gas turbine combustor, air is mixed with the gas fuel and expanded in a downstream burner tube. Introduction of air, passing downstream from the tip of the nozzle to the burner tube space forces hot gases away from and cools the nozzle tip. Air flow through an inner swirler or through cooling holes on the nozzle tip may be arranged to establish a cooling flow volume and direction that advantageously interacts with gas fuel-air flow from an outer swirler to improve fuel-air mixing in the burner tube, helping to reduce emissions and soot formation.
Abstract translation: 在用于燃气轮机燃烧器的空气扩散喷嘴中，空气与气体燃料混合并在下游燃烧器管中膨胀。 引入空气，从喷嘴的尖端下游到燃烧器管空间迫使热气体远离并冷却喷嘴尖端。 可以布置通过内旋流器或通过喷嘴尖端上的冷却孔的空气流，以建立冷却流体积和方向，其有利地与来自外旋流器的气体燃料 - 空气流相互作用以改善燃烧器管中的燃料 - 空气混合，帮助 以减少排放和烟灰形成。
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公开(公告)号：US20130115564A1
公开(公告)日：2013-05-09
申请号：US13289499
申请日：2011-11-04
Applicant: Satish Akkur Marigowda , Karthick Kaleeswaran , Venugopal Polisetty , Ajay Kumar Verma
Abstract: A combustion burner and a nozzle tip to a combustion burner is disclosed. The nozzle tip includes a face and at least one passage at the face enabling a gas impinging on the face to flow through the nozzle tip. At least one rib extends from the face to transfer heat from the nozzle tip to the impinging gas. The at least one rib extending from the face of the nozzle tip provides a surface area of the face that is greater than the surface area of a planar face. The nozzle tip can be coupled to an end of a nozzle of the combustion burner. The gas can be an air and/or an air/fuel mixture.
Abstract translation: 公开了燃烧器和燃烧器的喷嘴头。 喷嘴尖端包括一个表面和在该表面上的至少一个通道，使得气体能够撞击在该表面上以流过该喷嘴尖端。 至少一个肋从表面延伸以将热量从喷嘴尖端传递到冲击气体。 从喷嘴尖端的表面延伸出的至少一个肋提供面的表面面积大于平面的表面积。 喷嘴尖端可以联接到燃烧器的喷嘴的端部。 气体可以是空气和/或空气/燃料混合物。
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14.发明申请FULLY IMPINGEMENT COOLED VENTURI WITH INBUILT RESONATOR FOR REDUCED DYNAMICS AND BETTER HEAT TRANSFER CAPABILITIES 有权充分的冲击冷却VENTURI与减少动力学和更好的热传递能力的建筑谐振器公开(公告)号：US20120272654A1
公开(公告)日：2012-11-01
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
IPC: F02C1/00
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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公开(公告)号：US20120208141A1
公开(公告)日：2012-08-16
申请号：US13026373
申请日：2011-02-14
Applicant: Prabhu Kumar Ippadi Siddagangaiah , Kodukulla Venkat Sridhar , Karthick Kaleeswaran , Nitin Subramanya Sarja
Inventor： Prabhu Kumar Ippadi Siddagangaiah , Kodukulla Venkat Sridhar , Karthick Kaleeswaran , Nitin Subramanya Sarja
IPC: F23R3/44
CPC classification number: F23R3/002
Abstract: A combustor includes a combustion chamber and a liner surrounding the combustion chamber. A ridge on top of the liner extends continuously around the liner. In alternate embodiments, a ridge extends continuously around the liner, and a groove extends continuously around the liner adjacent to the ridge, wherein both of the ridge and the groove are either substantially flat or curved.
Abstract translation: 燃烧器包括燃烧室和围绕燃烧室的衬套。 衬套顶部的一个脊部围绕衬套连续延伸。 在替代实施例中，脊部围绕衬套连续延伸，并且凹槽围绕衬垫连续延伸，邻近脊部，其中脊部和凹槽都基本上平坦或弯曲。
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Patent Agency Ranking
公开(公告)号：US20120137696A1
公开(公告)日：2012-06-07
申请号：US12960767
申请日：2010-12-06
Applicant: Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
Inventor： Anand Prafulchandra Desai , Karthick Kaleeswaran , Venugopal Polisetty
IPC: F02C7/22
Abstract: In an air-staged diffusion nozzle for a gas turbine combustor, air is mixed with the gas fuel and expanded in a downstream burner tube. Introduction of air, passing downstream from the tip of the nozzle to the burner tube space forces hot gases away from and cools the nozzle tip. Air flow through an inner swirler or through cooling holes on the nozzle tip may be arranged to establish a cooling flow volume and direction that advantageously interacts with gas fuel-air flow from an outer swirler to improve fuel-air mixing in the burner tube, helping to reduce emissions and soot formation.
Abstract translation: 在用于燃气轮机燃烧器的空气扩散喷嘴中，空气与气体燃料混合并在下游燃烧器管中膨胀。 引入空气，从喷嘴的尖端下游到燃烧器管空间迫使热气体远离并冷却喷嘴尖端。 可以布置通过内旋流器或通过喷嘴尖端上的冷却孔的空气流，以建立冷却流体积和方向，其有利地与来自外旋流器的气体燃料 - 空气流相互作用以改善燃烧器管中的燃料 - 空气混合，帮助 以减少排放和烟灰形成。
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公开(公告)号：US20100300116A1
公开(公告)日：2010-12-02
申请号：US12473312
申请日：2009-05-28
Applicant: Karthick Kaleeswaran , Ganesh Pejawar Rao
Inventor： Karthick Kaleeswaran , Ganesh Pejawar Rao
IPC: F02C7/20
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：US20100236248A1
公开(公告)日：2010-09-23
申请号：US12406657
申请日：2009-03-18
Applicant: Karthick Kaleeswaran , Ganesh Pejawar Rao , Pankaj Kumar Jha
Inventor： Karthick Kaleeswaran , Ganesh Pejawar Rao , Pankaj Kumar Jha
IPC: F02C1/00
CPC classification number: F23R3/06 , F23R2900/00005
Abstract: A combustor liner for a gas turbine combustor includes a cooling hole formed in the liner that delivers cooling air into a combustion zone of the combustor. A stub is secured in the cooling hole and is structured to provide added stiffness to an inside edge of the cooling hole. The added stiffness reduces cracking caused by thermal fatigue and provides resistance against high cycle fatigue failures at high frequencies.
Abstract translation: 用于燃气轮机燃烧器的燃烧器衬套包括形成在衬套中的冷却孔，其将冷却空气输送到燃烧器的燃烧区。 短管被固定在冷却孔中并被构造成为冷却孔的内边缘提供附加的刚性。 增加的刚度可减少由热疲劳引起的裂纹，并提供高频时高循环疲劳失效的阻力。
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19.发明申请公开(公告)号：US20090255268A1
公开(公告)日：2009-10-15
申请号：US12081167
申请日：2008-04-11
Applicant: Karthick Kaleeswaran , Ganesh Pejawar Rao
Inventor： Karthick Kaleeswaran , Ganesh Pejawar Rao
IPC: F02C1/00
CPC classification number: F23R3/002
Abstract: A cooling arrangement for a turbine combustor liner includes a combustor liner; a flow sleeve surrounding at least a portion of the combustor liner with a flow annulus therebetween, the flow sleeve having a plurality of rows of cooling holes formed about a circumference thereof for directing cooling air into the flow annulus and toward the combustor liner. One or more of the cooling holes is fitted with a thimble extending in a radial direction toward the combustor liner, the thimble having a peripheral wall diverging in a direction of flow of the cooling air.
Abstract translation: 涡轮燃烧器衬套的冷却装置包括燃烧器衬套; 围绕所述燃烧器衬套的至少一部分的流动套筒，其间具有流动环空，所述流动套筒具有围绕其圆周形成的多排冷却孔，用于将冷却空气引导到所述流动环空中并朝向所述燃烧器衬套。 一个或多个冷却孔装配有朝向燃烧器衬套沿径向延伸的套管，套管具有在冷却空气的流动方向上分流的周壁。
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公开(公告)号：US20080282667A1
公开(公告)日：2008-11-20
申请号：US11750500
申请日：2007-05-18
Applicant: John Charles Intile , Madhavan Poyyapakkam , Ganesh Pejawar Rao , Karthick Kaleeswaran
IPC: F02C7/18
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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