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公开(公告)号：US20090188255A1
公开(公告)日：2009-07-30
申请号：US12247615
申请日：2008-10-08
申请人： Andrew Green , Peter Stuttaford , Yan Chen , Hany Rizkalla
发明人： Andrew Green , Peter Stuttaford , Yan Chen , Hany Rizkalla
CPC分类号： F01D9/023 , F23R3/002 , F23R3/283 , F23R3/286 , F23R2900/03041 , F23R2900/03044
摘要： A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.
摘要翻译： 公开了一种具有改进的冷却结构的燃烧器端盖组件。 本发明的实施例涉及一种用于冷却燃烧器端盖组件的渗出板的装置和方法。 燃烧器端盖组件还包括具有多个冷却孔的冲击板，冲击板定位在距离排出板预定距离处。 冷却流体通过冲击板并且朝向和朝向积液板上并用于冷却渗出板。
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公开(公告)号：US08438853B2
公开(公告)日：2013-05-14
申请号：US12247615
申请日：2008-10-08
申请人： Andrew Green , Peter Stuttaford , Yan Chen , Hany Rizkalla
发明人： Andrew Green , Peter Stuttaford , Yan Chen , Hany Rizkalla
CPC分类号： F01D9/023 , F23R3/002 , F23R3/283 , F23R3/286 , F23R2900/03041 , F23R2900/03044
摘要： A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.
摘要翻译： 公开了一种具有改进的冷却结构的燃烧器端盖组件。 本发明的实施例涉及一种用于冷却燃烧器端盖组件的渗出板的装置和方法。 燃烧器端盖组件还包括具有多个冷却孔的冲击板，冲击板定位在距离排出板预定距离处。 冷却流体通过冲击板并且朝向和朝向积液板上并用于冷却渗出板。
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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：US06898937B2
公开(公告)日：2005-05-31
申请号：US10452449
申请日：2003-06-02
CPC分类号： F23R3/286 , F23D2214/00 , F23D2900/00008 , F23D2900/14004
摘要： A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.
摘要翻译： 公开了一种用于燃气轮机燃烧器中的预混燃料喷嘴和操作方法。 预混合燃料喷嘴利用包括多个径向延伸的翅片的翅片组件，用于喷射燃料和压缩空气，以提供更均匀的喷射模式。 燃料和压缩空气在燃烧室的上游混合并作为均匀的混合物流入燃烧室。 预混合燃料喷嘴包括多个同轴通道，其向燃料组件提供燃料和压缩空气，以及压缩空气以冷却喷嘴盖组件。 替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加燃料喷射区域。 公开了第二替代实施例，其重新配置喷射器组件和燃料喷射位置以最小化喷射器组件处的流动阻塞问题。
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公开(公告)号：US06915636B2
公开(公告)日：2005-07-12
申请号：US10465096
申请日：2003-06-19
CPC分类号： F23L7/002 , F23D2209/30 , F23D2214/00 , F23D2900/00008 , F23D2900/14004 , F23R3/286 , F23R3/36
摘要： A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly and simplify fuel nozzle manufacturing.
摘要翻译： 公开了一种用于燃气轮机燃烧器的双燃料预混喷嘴和操作方法。 双燃料预混喷嘴利用一种翅片组件，其包括多个径向延伸的翅片，用于喷射气体燃料和压缩空气，以便提供更均匀的注射模式和均匀的混合物。 预混合燃料喷嘴包括多个同轴通道，其向翅片组件提供气体燃料和压缩空气。 当处于液体燃料运行时，气体回路用压缩空气吹扫，液体燃料和水通过同轴通道到达双燃料预混燃料喷嘴的末端，在那里它们将液体燃料和水注入到二次燃烧室中。 替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加气体燃料喷射区域。 公开了第二替代实施例，其重新配置喷射器组件和燃料喷射位置以最小化喷射器组件处的流动阻塞问题并简化燃料喷嘴制造。
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公开(公告)号：US08731797B2
公开(公告)日：2014-05-20
申请号：US13086978
申请日：2011-04-14
IPC分类号： B60T7/12
摘要： A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine, and for dynamically tuning the GT engine as a function of changes to the monitored fuel properties. Initially, readings are taken from the GT engine during a reference calibration, or commissioning, and utilized to calculate an initial-pressure-drop reference value. The tuning process during commercial operation takes post-calibration readings from the GT engine to calculate a fuel property parameter, which represents a heating value of the fuel. Specifically, the fuel property parameter is calculated by deriving a corrected-pressure-drop dynamic value as a function of pressure and temperature readings of the fuel at a point upstream of a combustor and pressure drops across fuel nozzles that introduce the fuel into the combustor, and solving a ratio of the dynamic value and the reference value.
摘要翻译： 提供了一种调节过程，用于监测由燃气轮机（GT）发动机消耗的燃料的燃料性质，并且用于根据对所监测的燃料性质的变化来动态调节GT发动机。 最初，在参考校准或调试期间从GT发动机获取读数，并用于计算初始压降参考值。 商业运行过程中的调整过程需要GT发动机的后校准读数，以计算燃料特性参数，该参数代表燃料的热值。 具体地说，燃料特性参数通过导出作为燃料在燃烧器上游一点上燃料的压力和温度读数的函数的校正压降动态值来计算，并且将燃料引入燃烧器的燃料喷嘴之间的压力下降， 并求解动态值和参考值的比值。
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公开(公告)号：US08136359B2
公开(公告)日：2012-03-20
申请号：US11953162
申请日：2007-12-10
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23D2900/00008 , F23R2900/00001 , F23R2900/00005
摘要： Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
摘要翻译： 公开了用于使燃气轮机燃烧器的燃料喷嘴内的相对热增长最小化的实施例。 提供了一种燃料喷嘴结构，其中加热流体从燃料喷嘴基座中的进料孔设置在燃料喷嘴中的一个或多个通道中。 加热流体通过燃料喷嘴，从而提高燃料喷嘴部分的工作温度，以减少燃料喷嘴内热梯度的差异。 还公开了各种燃料喷嘴构造和通道几何形状。
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公开(公告)号：US20090145983A1
公开(公告)日：2009-06-11
申请号：US11953162
申请日：2007-12-10
IPC分类号： F02M61/18
CPC分类号： F23R3/286 , F23D2900/00008 , F23R2900/00001 , F23R2900/00005
摘要： Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
摘要翻译： 公开了用于使燃气轮机燃烧器的燃料喷嘴内的相对热增长最小化的实施例。 提供了一种燃料喷嘴结构，其中加热流体从燃料喷嘴基座中的进料孔设置在燃料喷嘴中的一个或多个通道中。 加热流体通过燃料喷嘴，从而提高燃料喷嘴部分的工作温度，以减少燃料喷嘴内热梯度的差异。 还公开了各种燃料喷嘴构造和通道几何形状。
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公开(公告)号：US20090145137A1
公开(公告)日：2009-06-11
申请号：US12196629
申请日：2008-08-22
IPC分类号： F02C7/00
CPC分类号： F01D9/023 , F01D25/28 , F05D2230/642 , F05D2260/96
摘要： A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.
摘要翻译： 公开了一种具有无热的后框架和用于燃气涡轮发动机的安装系统的过渡管道组件。 后框架能够调节到热梯度，而安装系统在发动机组装期间至少提供过渡管道的横向移动。 安装系统还提供了一种用于提高过渡管道在发动机动态励磁范围之外的固有频率的装置。
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