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公开(公告)号：US07386980B2
公开(公告)日：2008-06-17
申请号：US10906074
申请日：2005-02-02
CPC分类号： F23R3/42 , F23R3/005 , Y02T50/675
摘要： A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to a passing cooling medium is increased, thereby increasing the heat transfer through the combustion liner. Multiple embodiments of textured patterns are also disclosed.
摘要翻译： 公开了一种在衬套的至少一部分上具有增强的热传递的燃烧衬套。 除了其它特征之外，燃烧衬套包括外表面，其中外表面的至少一个区域以基本均匀的图案纹理化，使得暴露于通过的冷却介质的表面积增加，从而增加通过燃烧的热传递 衬垫。 还公开了纹理图案的多个实施例。
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公开(公告)号：US20060168965A1
公开(公告)日：2006-08-03
申请号：US10906074
申请日：2005-02-02
IPC分类号： F23R3/42
CPC分类号： F23R3/42 , F23R3/005 , Y02T50/675
摘要： A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to a passing cooling medium is increased, thereby increasing the heat transfer through the combustion liner. Multiple embodiments of textured patterns are also disclosed.
摘要翻译： 公开了一种在衬套的至少一部分上具有增强的热传递的燃烧衬套。 除了其它特征之外，燃烧衬套包括外表面，其中外表面的至少一个区域以基本均匀的图案纹理化，使得暴露于通过的冷却介质的表面积增加，从而增加通过燃烧的热传递 衬垫。 还公开了纹理图案的多个实施例。
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公开(公告)号：US20050262844A1
公开(公告)日：2005-12-01
申请号：US10856592
申请日：2004-05-28
CPC分类号： F23R3/002 , F01D9/023 , F23R3/46 , Y02T50/675
摘要： A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.
摘要翻译： 公开了一种燃气轮机燃烧衬套，其在其与过渡管道之间具有交替的界面区域，其中沿着燃烧衬套的后端的冷却效果和热传递得到改善，导致部件寿命延长。 靠近其第二端的燃烧衬套的区域包括多个第一进料孔，密封过渡管道的多个弹簧密封件，具有多个第二进料孔的冷却环，其中第一进料孔通过冷却 流体进入形成在冷却环和燃烧衬套之间的环形空间中。 冷却流体越过用于增加靠近燃烧衬套第二端的热传递的装置，其中传热增强优选地包括多个凸脊，其增加外衬套壁的表面积以使冷却流体紊乱并使冷却最大化 有效性
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公开(公告)号：US07007482B2
公开(公告)日：2006-03-07
申请号：US10856592
申请日：2004-05-28
IPC分类号： F02C7/12
CPC分类号： F23R3/002 , F01D9/023 , F23R3/46 , Y02T50/675
摘要： A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.
摘要翻译： 公开了一种燃气轮机燃烧衬套，其在其与过渡管道之间具有交替的界面区域，其中沿着燃烧衬套的后端的冷却效果和热传递得到改善，导致部件寿命延长。 靠近其第二端的燃烧衬套的区域包括多个第一进料孔，密封过渡管道的多个弹簧密封件，具有多个第二进料孔的冷却环，其中第一进料孔通过冷却 流体进入形成在冷却环和燃烧衬套之间的环形空间中。 冷却流体越过用于增加靠近燃烧衬套第二端的热传递的装置，其中传热增强优选地包括多个凸脊，其增加外衬套壁的表面积以使冷却流体紊乱并使冷却最大化 有效性
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公开(公告)号：US07677025B2
公开(公告)日：2010-03-16
申请号：US10906057
申请日：2005-02-01
申请人： Peter Stuttaford , Stephen Jennings
发明人： Peter Stuttaford , Stephen Jennings
IPC分类号： F02C3/00
CPC分类号： F23R3/343 , F02C7/22 , F05D2260/60 , F23D2209/30
摘要： A gas turbine combustor having a self-purging pilot fuel injection system and method of operation thereof is disclosed. The pilot fuel injection system comprises a radial inflow swirler, a generally axially extending centerbody, and at least one fuel injection source. In operation a fluid containing at least air passes along the centerbody outer surface clearing any remaining fuel from proximate the fuel injection source so as to prevent flame attachment proximate the fuel injection source.
摘要翻译： 公开了一种具有自净化引燃燃料喷射系统及其操作方法的燃气轮机燃烧器。 引燃燃料喷射系统包括径向流入旋流器，大致轴向延伸的中心体和至少一个燃料喷射源。 在操作中，至少含有空气的流体沿着中心体外表面通过，从燃料喷射源的附近清除任何剩余的燃料，以便防止燃料喷射源附近的火焰附着。
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6.发明授权公开(公告)号：US07137256B1
公开(公告)日：2006-11-21
申请号：US10906631
申请日：2005-02-28
IPC分类号： F02C9/00
摘要： A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type combustor having alternate ignition techniques of spark ignition or torch ignition.
摘要翻译： 公开了一种在维持所需排放水平的同时在较低负载条件下操作燃气涡轮发动机燃烧系统的方法。 本发明包括在具有火花点火或火炬点火的交替点火技术的罐型燃烧器内的轴向，径向和周向燃料分级的多个实施例。
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公开(公告)号：US20090145099A1
公开(公告)日：2009-06-11
申请号：US11951790
申请日：2007-12-06
CPC分类号： F01D25/12 , F01D9/023 , F05D2260/20 , F05D2260/201
摘要： Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
摘要翻译： 公开了用于向燃气轮机过渡管道提供冷却流体以降低过渡管道的有效操作温度的装置和相关方法的实施例。 过渡管道具有内衬和径向向外定位的冲击套筒，其间形成有通道。 冲击套筒具有多个开口，其中开口的一部分各自具有延伸穿过开口并进入通道的进料管。 进料管相对于冲击套筒定向成一定角度，使得进料管的入口通常朝着迎面而来的冷却流体流动。 进料管将一部分冷却流体引向内衬并进入通道以冷却过渡管道。
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公开(公告)号：US08151570B2
公开(公告)日：2012-04-10
申请号：US11951790
申请日：2007-12-06
IPC分类号： F02C1/00
CPC分类号： F01D25/12 , F01D9/023 , F05D2260/20 , F05D2260/201
摘要： Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
摘要翻译： 公开了用于向燃气轮机过渡管道提供冷却流体以降低过渡管道的有效操作温度的装置和相关方法的实施例。 过渡管道具有内衬和径向向外定位的冲击套筒，其间形成有通道。 冲击套筒具有多个开口，其中开口的一部分各自具有延伸穿过开口并进入通道的进料管。 进料管相对于冲击套筒定向成一定角度，使得进料管的入口通常朝着迎面而来的冷却流体流动。 进料管将一部分冷却流体引向内衬并进入通道以冷却过渡管道。
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公开(公告)号：US20060150634A1
公开(公告)日：2006-07-13
申请号：US10905497
申请日：2005-01-07
IPC分类号： F23R3/30
摘要： The present invention discloses an apparatus and method for reducing the carbon monoxide emissions emitted by a pilot injector of a gas turbine combustor. Multiple embodiments of a means for establishing a recirculation zone are disclosed whereby a portion of the fuel and air mixture from the pilot injector recirculates and a flame is held, thereby increasing the local reaction temperature at the desired location and lowering carbon monoxide emissions.
摘要翻译： 本发明公开了一种用于减少由燃气轮机燃烧器的先导喷射器排出的一氧化碳排放的装置和方法。 公开了用于建立再循环区的装置的多个实施例，其中来自先导喷射喷射器的燃料和空气混合物的一部分再循环并保持火焰，由此增加所需位置处的局部反应温度并降低一氧化碳排放。
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公开(公告)号：US07308793B2
公开(公告)日：2007-12-18
申请号：US10905497
申请日：2005-01-07
IPC分类号： F23R3/14
摘要： The present invention discloses an apparatus and method for reducing the carbon monoxide emissions emitted by a pilot injector of a gas turbine combustor. Multiple embodiments of a means for establishing a recirculation zone are disclosed whereby a portion of the fuel and air mixture from the pilot injector recirculates and a flame is held, thereby increasing the local reaction temperature at the desired location and lowering carbon monoxide emissions.
摘要翻译： 本发明公开了一种用于减少由燃气轮机燃烧器的先导喷射器排出的一氧化碳排放的装置和方法。 公开了用于建立再循环区的装置的多个实施例，其中来自先导喷射喷射器的燃料和空气混合物的一部分再循环并保持火焰，由此增加所需位置处的局部反应温度并降低一氧化碳排放。
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