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1. 发明申请

US20050262844A1 COMBUSTION LINER SEAL WITH HEAT TRANSFER AUGMENTATION 有权
标题翻译：燃烧内衬密封带热传递补偿
公开(公告)号：US20050262844A1
公开(公告)日：2005-12-01
申请号：US10856592
申请日：2004-05-28
申请人： Andrew Green , Peter Stuttaford , Jeffrey Benoit , Vamsi Duraibabu , Hany Rizkalla
发明人： Andrew Green , Peter Stuttaford , Jeffrey Benoit , Vamsi Duraibabu , Hany Rizkalla
IPC分类号： F01D9/02 , F23R3/00 , F23R3/42 , F23R3/46
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

2. 发明授权

US07007482B2 Combustion liner seal with heat transfer augmentation 有权
标题翻译：具有传热增强的燃烧衬套密封
公开(公告)号：US07007482B2
公开(公告)日：2006-03-07
申请号：US10856592
申请日：2004-05-28
申请人： Andrew Green , Peter Stuttaford , Jeffrey Arthur Benoit , Vamsi Duraibabu , Hany Rizkalla
发明人： Andrew Green , Peter Stuttaford , Jeffrey Arthur Benoit , Vamsi Duraibabu , Hany Rizkalla
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

3. 发明授权

US07386980B2 Combustion liner with enhanced heat transfer 有权
标题翻译：具有增强热传递的燃烧衬管
公开(公告)号：US07386980B2
公开(公告)日：2008-06-17
申请号：US10906074
申请日：2005-02-02
申请人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
发明人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
IPC分类号： F02C1/00 , F02G3/00
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。

4. 发明申请

US20060168965A1 Combustion Liner with Enhanced Heat Transfer 有权
标题翻译：具有增强热传递的燃烧衬管
公开(公告)号：US20060168965A1
公开(公告)日：2006-08-03
申请号：US10906074
申请日：2005-02-02
申请人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
发明人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
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。

5. 发明申请

US20090188255A1 COMBUSTOR END CAP ASSEMBLY 有权
标题翻译： COMBUSTOR端盖总成
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
IPC分类号： F02C7/12 , F23R3/32
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。

6. 发明授权

US08438853B2 Combustor end cap assembly 有权
标题翻译：燃烧器端盖组件
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
IPC分类号： F02C1/00 , F02G3/00
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。

7. 发明授权

US06898937B2 Gas only fin mixer secondary fuel nozzle 有权
标题翻译：燃气只有翅片混合器二次燃料喷嘴
公开(公告)号：US06898937B2
公开(公告)日：2005-05-31
申请号：US10452449
申请日：2003-06-02
申请人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
发明人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
IPC分类号： F23R3/28 , F02C7/22
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。

8. 发明授权

US06915636B2 Dual fuel fin mixer secondary fuel nozzle 有权
标题翻译：双燃料翅片混合器二次燃油喷嘴
公开(公告)号：US06915636B2
公开(公告)日：2005-07-12
申请号：US10465096
申请日：2003-06-19
申请人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
发明人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
IPC分类号： F23L7/00 , F23R3/28 , F23R3/36 , F02C1/00 , F02G3/00
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。

9. 发明授权

US08731797B2 Employing fuel properties to auto-tune a gas turbine engine 有权
标题翻译：采用燃油特性自动调节燃气轮机
公开(公告)号：US08731797B2
公开(公告)日：2014-05-20
申请号：US13086978
申请日：2011-04-14
申请人： Nicolas Demougeot , Donald Gauthier , Peter Stuttaford , Hany Rizkalla
发明人： Nicolas Demougeot , Donald Gauthier , Peter Stuttaford , Hany Rizkalla
IPC分类号： B60T7/12
CPC分类号： F02C7/224 , F02C9/28 , F02C9/40
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。

10. 发明授权

US08136359B2 Gas turbine fuel nozzle having improved thermal capability 有权
标题翻译：具有改善的热能的燃气轮机燃料喷嘴
公开(公告)号：US08136359B2
公开(公告)日：2012-03-20
申请号：US11953162
申请日：2007-12-10
申请人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
发明人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
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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