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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：US06935116B2
公开(公告)日：2005-08-30
申请号：US10424350
申请日：2003-04-28
申请人： Peter J. Stuttaford , Stephen Jennings , Andrew Green , Ryan McMahon , Yan Chen , Hany Rizkalla , John Carella , Vamsi Duraibabu , Martin Spalding
发明人： Peter J. Stuttaford , Stephen Jennings , Andrew Green , Ryan McMahon , Yan Chen , Hany Rizkalla , John Carella , Vamsi Duraibabu , Martin Spalding
摘要： A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, and precise three dimensional staging between fuel injectors. Axial, radial, and circumferential fuel staging is utilized including fuel injection proximate air swirlers. Furthermore, strong recirculation zones are established proximate the introduction of fuel and air premixture from different stages to the combustion zone. The combination of the strong recirculation zones, efficient premixing, and staged fuel flow thereby provide the opportunity to produce low emissions combustion at various load conditions.
摘要翻译： 公开了一种在多个负载条件下具有减少的排放和改进的火焰稳定性的燃气轮机燃烧系统。 改进的燃烧系统通过完全预混合，多个燃料喷射器位置，燃烧器几何形状和燃料喷射器之间的精确三维分级来实现。 使用轴向，径向和周向燃料分级，包括靠近空气旋流器的燃料喷射。 此外，在从不同阶段到燃烧区的燃料和空气预混物的引入附近建立强的再循环区域。 强再循环区域的组合，有效的预混合和分级燃料流量因此提供在各种负载条件下产生低排放燃烧的机会。
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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：US20120023953A1
公开(公告)日：2012-02-02
申请号：US12844280
申请日：2010-07-27
IPC分类号： F02C9/00
CPC分类号： F02C7/228 , F02C9/28 , Y02T50/672
摘要： Methods for controlling fuel splits to a combustor of a gas turbine are disclosed. The methods may include determining a combustion reference temperature of the gas turbine, measuring a biasing parameter of the gas turbine, determining at least one fuel split biasing value based on the combustion reference temperature and the biasing parameter and adjusting a nominal fuel split schedule based on the at least one fuel split biasing value.
摘要翻译： 公开了用于控制燃料分流到燃气轮机的燃烧器的方法。 所述方法可以包括确定燃气轮机的燃烧参考温度，测量燃气轮机的偏置参数，基于燃烧参考温度和偏置参数确定至少一个燃料分离偏置值，并基于 所述至少一个燃料分流偏置值。
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