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公开(公告)号：US20050262845A1
公开(公告)日：2005-12-01
申请号：US10857713
申请日：2004-05-28
申请人： Vincent Martling , Zhenhua Xiao
发明人： Vincent Martling , Zhenhua Xiao
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 along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner proximate its second end comprises a plurality of spring seals that seal against a transition duct while admitting a cooling fluid to pass into a passage, formed between the combustion liner and spring seals, that feeds a plurality of cooling holes located in the combustion liner proximate the liner second end. Depending on the cooling requirements, the cooling holes can be angled both axially and circumferentially to 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替代的界面区域，其中沿着燃烧衬套的后端的冷却效果得到改善，从而在使用更简单的燃烧衬套几何形状的同时延长了部件的使用寿命。 靠近其第二端的燃烧衬套的区域包括多个弹簧密封件，其在允许冷却流体进入形成在燃烧衬套和弹簧密封件之间的通道中时密封过渡管道，该通道供给多个位于 在靠近衬套第二端的燃烧衬里中。 根据冷却要求，冷却孔可以轴向和周向成角度，以最大化冷却效果。
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公开(公告)号：US20050198965A1
公开(公告)日：2005-09-15
申请号：US10799970
申请日：2004-03-12
申请人： John Henriquez , Jacob McLeroy , Brian Mack , Vincent Martling
发明人： John Henriquez , Jacob McLeroy , Brian Mack , Vincent Martling
IPC分类号： F23R3/42
CPC分类号： F23R3/286 , F23R3/16 , F23R3/283 , F23R3/36 , F23R2900/00004
摘要： A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.
摘要翻译： 公开了一种燃料喷嘴和燃气轮机燃烧器，其能够对燃料喷嘴和相邻的燃烧器部件的碳积累减少的多种燃料进行操作。 燃料喷嘴包括重新配置的气体燃料组件和混合管，以消除已知的再循环区域。 此外，液体燃料组件包括重新配置的喷雾特性，以进一步减少与混合管的液滴相互作用。
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公开(公告)号：US20050241321A1
公开(公告)日：2005-11-03
申请号：US10836972
申请日：2004-04-30
申请人： Vincent Martling , Zhenhua Xiao
发明人： Vincent Martling , Zhenhua Xiao
CPC分类号： F23R3/002 , F01D9/023 , F05D2260/202 , F05D2260/203 , F05D2260/221 , F23R2900/03041
摘要： A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine inlet. The first panel includes a means for augmenting the heat transfer from the first panel while the second panel includes a plurality of first cooling holes for directing cooling air through the second panel. Specific details are provided regarding the first cooling holes and multiple embodiments are disclosed for the heat transfer augmentation of the transition duct first panel.
摘要翻译： 公开了一种具有减小的压力损失的燃气轮机过渡管道。 优选实施例的过渡管道包括面板组件，其具有固定到第二面板的第一面板和用于将过渡管道固定到涡轮机入口的安装组件。 第一面板包括用于增加从第一面板传热的装置，而第二面板包括用于引导冷却空气通过第二面板的多个第一冷却孔。 提供关于第一冷却孔的具体细节，并且公开了多个实施例用于过渡管道第一面板的传热增强。
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4.发明申请公开(公告)号：US20050241317A1
公开(公告)日：2005-11-03
申请号：US10836971
申请日：2004-04-30
申请人： Vincent Martling , Zhenhua Xiao
发明人： Vincent Martling , Zhenhua Xiao
摘要： The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient turbine and increased engine output. Significant enhancements include the addition of a plurality of deflector assemblies to direct the air from a compressor outlet towards an exposed single-wall transition duct to provide direct cooling to a first panel of the transition duct.
摘要翻译： 本发明提供了一种用于在进入燃烧系统之前减少空气的压力损失的装置和方法，使得对于具有预定压力损失的已知燃烧系统，进入涡轮机的所得流体具有较高的供应压力，这将导致 在更高效的涡轮机和增加的发动机输出。 显着的增强包括添加多个偏转器组件以将空气从压缩机出口朝向暴露的单壁过渡管道引导，以向过渡管道的第一面板提供直接冷却。
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公开(公告)号：US20050144953A1
公开(公告)日：2005-07-07
申请号：US10746310
申请日：2003-12-24
CPC分类号： F23R3/34 , F23R3/04 , F23R2900/03042
摘要： A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured to incorporate a conical aft portion having a plurality of air feed holes that reduce pressure loss to the incoming air and flow separation effects from the surrounding combustor hardware, thereby resulting in improved combustor performance.
摘要翻译： 公开了一种具有改善的冷却效率和寿命的燃气轮机燃烧器结构以及用于提高冷却效率的方法。 燃气轮机燃烧器结合了独特的流动套管结构，用于引导空气更有效地冷却燃烧衬套。 流动套管几何结构被构造成结合了具有多个空气供给孔的锥形后部部分，其减少了来自周围燃烧器硬件的进入空气的压力损失和流动分离效应，由此导致改进的燃烧室性能。
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公开(公告)号：US20050132708A1
公开(公告)日：2005-06-23
申请号：US10744423
申请日：2003-12-22
申请人： Vincent Martling , Zhenhua Xiao
发明人： Vincent Martling , Zhenhua Xiao
CPC分类号： F23R3/60 , F01D9/023 , F23D2211/00 , F23D2214/00 , F23R2900/00005 , F23R2900/03041
摘要： An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.
摘要翻译： 公开了燃气轮机燃烧器的燃烧衬套和过渡管道之间的界面区域，其具有改进的冷却，使得部件寿命增加并且金属温度降低。 燃烧衬套的后端可伸缩地容纳在过渡管道内，使得燃烧衬套密封件与过渡管道入口环的内壁接触。 增加燃烧衬套后端的专用冷却空气供应，与改进的燃烧衬套后端几何结合，显着减少湍流和流动再循环，从而导致更低的金属温度和增加的部件寿命。 取决于所需的冷却量来公开界面区域的多个实施例。
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