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111. 发明公开

US20230408094A1 TRAILING EDGE FUEL INJECTION ENHANCEMENT FOR FLAME HOLDING MITIGATION 审中-公开
公开(公告)号：US20230408094A1
公开(公告)日：2023-12-21
申请号：US17980215
申请日：2022-11-03
申请人： Power Systems Mfg., LLC
发明人： Dwain TERREL , Matthew YAQUINTO , Fred HERNANDEZ , Hany RIZKALLA , Nicolas DEMOUGEOT , Peter John STUTTAFORD
IPC分类号： F23R3/28 , F23R3/14
CPC分类号： F23R3/286 , F23R3/14 , F05D2250/184 , F05D2250/14 , F05D2240/35
摘要： An injector for a combustor of a gas turbine engine is provided with a plurality of first vanes radially arrayed about a central axis of the injector and a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes. A plurality of fuel injection holes are disposed nearer to a trailing edge than to a leading edge of the second vanes for injecting fuel into compressed air passing through over the second vanes. The trailing edge of each of the second vanes includes a non-planar profile configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air and reduce the surfaces on which undesirable flame anchoring may occur.

112. 发明授权

US11629616B1 Radially flexible flange joint for exhaust manifold 有权
公开(公告)号：US11629616B1
公开(公告)日：2023-04-18
申请号：US17674268
申请日：2022-02-17
申请人： Power Systems Mfg., LLC
发明人： Brian John Loucks , Kevin Carpenter , Kevin Powell
IPC分类号： F01D25/30 , F16L27/11 , F16J15/08
摘要： A radially flexible connection joint for a gas turbine engine includes an exhaust manifold flange operatively coupling an exhaust cylinder to an exhaust manifold of the gas turbine engine. The exhaust cylinder includes a cylindrical flange that extends radially outwardly from a rotation axis of the gas turbine. The cylindrical flange defines a downstream axial face. The exhaust manifold is positioned downstream from the exhaust cylinder. The exhaust manifold includes an upstream edge. The exhaust cylinder and the exhaust manifold are substantially coaxial with the rotation axis of the gas turbine. The exhaust manifold flange has a bellows portion that extends radially between the cylindrical flange of the exhaust cylinder and the upstream edge of the exhaust manifold. The bellows portion permits relative radial motion of the exhaust cylinder and the exhaust manifold.

113. 发明申请

US20210189885A1 MODULAR COMPONENTS FOR GAS TURBINE ENGINES AND METHODS OF MANUFACTURING THE SAME 有权
公开(公告)号：US20210189885A1
公开(公告)日：2021-06-24
申请号：US16721292
申请日：2019-12-19
申请人： Power Systems Mfg., LLC
发明人： Gregory Edwin Vogel , Thomas Rosenbarger , Joshua R. McNally
IPC分类号： F01D5/14 , F01D5/28
摘要： Modular assemblies for gas turbine engines such as modular vane assemblies and methods of manufacturing the same. The modular assembly includes a first modular component such as a vane platform having a first mating pocket, and a second modular such as an airfoil. The second modular component includes circumferentially extending first and second surfaces at first and second distal ends thereof, respectively, with the first surface being received within the first pocket when the modular assembly is in the assembled state. The second modular component also includes a coating pocket extending from the first surface to the second surface. The coating pocket is recessed towards an interior of the second modular component with respect to first surface and the second surface, and a thermal barrier coating is included within the coating pocket and not included on the first surface or the surface.

114. 发明授权

US08504276B2 Gas turbine engine controls for minimizing combustion dynamics and emissions 有权
标题翻译：用于最小化燃烧动力学和排放的燃气轮机引擎控制
公开(公告)号：US08504276B2
公开(公告)日：2013-08-06
申请号：US12039183
申请日：2008-02-28
申请人： Vincent C. Martling , Peter So , Zhenhua Xiao , Plazi Ricklin
发明人： Vincent C. Martling , Peter So , Zhenhua Xiao , Plazi Ricklin
IPC分类号： F02M63/02
CPC分类号： F02C9/28 , F02C9/34 , F05D2270/082 , F05D2270/303 , F05D2270/708 , F23N2041/20
摘要： Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
摘要翻译：公开了用于控制燃气涡轮发动机以使燃烧动力学和排放最小化的实施例。提供了用于控制燃气涡轮发动机的方法和装置，其中测量压缩机入口温度并且实时计算涡轮参考温度，并用于确定每个燃料回路的最有效的燃料分流和运行条件。然后根据所识别的燃料分配来调节燃料回路的燃料流量。

115. 发明申请

US20090222187A1 GAS TURBINE ENGINE CONTROLS FOR MINIMIZING COMBUSTION DYNAMICS AND EMISSIONS 有权
标题翻译：用于最小化燃烧动力学和排放的气体涡轮发动机控制
公开(公告)号：US20090222187A1
公开(公告)日：2009-09-03
申请号：US12039183
申请日：2008-02-28
申请人： VINCENT C. MARTLING , Peter SO , ZHENHUA XIAO , PLAZI RICKLIN
发明人： VINCENT C. MARTLING , Peter SO , ZHENHUA XIAO , PLAZI RICKLIN
IPC分类号： F02C9/00
CPC分类号： F02C9/28 , F02C9/34 , F05D2270/082 , F05D2270/303 , F05D2270/708 , F23N2041/20
摘要： Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
摘要翻译：公开了用于控制燃气涡轮发动机以使燃烧动力学和排放最小化的实施例。提供了用于控制燃气涡轮发动机的方法和装置，其中测量压缩机入口温度并且实时计算涡轮参考温度，并用于确定每个燃料回路的最有效的燃料分流和运行条件。然后根据所识别的燃料分配来调节燃料回路的燃料流量。

116. 发明申请

US20090139237A1 Low residence combustor fuel nozzle 有权
标题翻译：低住宅燃烧器燃油喷嘴
公开(公告)号：US20090139237A1
公开(公告)日：2009-06-04
申请号：US11998769
申请日：2007-11-29
申请人： Daniel J. Sullivan , Peter Stuttaford , Robert J. Kraft , Khalid Oumejjoud , Yan Chen
发明人： Daniel J. Sullivan , Peter Stuttaford , Robert J. Kraft , Khalid Oumejjoud , Yan Chen
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R3/14
摘要： Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.
摘要翻译：公开了用于减少在燃气轮机燃烧器中的停留时间的设备和相关方法的实施例。本发明的实施例包括燃料喷嘴，其延伸到用于燃烧衬套的端盖的下游平面，其中预混合器的轴向距离减小，然而用于混合燃料和空气的涡流增加。结果，燃料和空气的混合基本上没有变化，从而允许在预混合器内更高的空气压力和操作温度而不引起自动点火。

117. 发明授权

US07308793B2 Apparatus and method for reducing carbon monoxide emissions 有权
标题翻译：减少一氧化碳排放的装置和方法
公开(公告)号：US07308793B2
公开(公告)日：2007-12-18
申请号：US10905497
申请日：2005-01-07
申请人： Khalid Oumejjoud , Peter Stuttaford , Yan Chen , Nuria Margarit-Bel , Stephen Jennings
发明人： Khalid Oumejjoud , Peter Stuttaford , Yan Chen , Nuria Margarit-Bel , Stephen Jennings
IPC分类号： F23R3/14
CPC分类号： F23C9/006 , F23R3/16 , F23R3/343
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。

118. 发明授权

US07229245B2 Vane platform rail configuration for reduced airfoil stress 有权
标题翻译：叶片平台导轨配置减少翼型应力
公开(公告)号：US07229245B2
公开(公告)日：2007-06-12
申请号：US10891400
申请日：2004-07-14
申请人： Charles A. Ellis , David Parker , J. Page Strohl , David Medrano
发明人： Charles A. Ellis , David Parker , J. Page Strohl , David Medrano
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2260/941
摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
摘要翻译：公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。这是通过沿着叶片组装轨道放置开口来实现的，其减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。

119. 发明授权

US07165405B2 Fully premixed secondary fuel nozzle with dual fuel capability 有权
标题翻译：具有双重燃料能力的完全预混合二次燃料喷嘴
公开(公告)号：US07165405B2
公开(公告)日：2007-01-23
申请号：US10195615
申请日：2002-07-15
申请人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Brian R. Mack
发明人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Brian R. Mack
IPC分类号： F23R3/30
CPC分类号： F23R3/286 , F23D2209/30 , F23D2900/00008 , F23D2900/14004 , 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 fuel and compressed air in order to provide a more uniform injection pattern. When in gas operation, 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 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.
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，用于喷射燃料和压缩空气，以提供更均匀的喷射模式。当在气体操作时，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。

120. 发明授权

US07137241B2 Transition duct apparatus having reduced pressure loss 有权
标题翻译：具有减小的压力损失的过渡管道装置
公开(公告)号：US07137241B2
公开(公告)日：2006-11-21
申请号：US10836972
申请日：2004-04-30
申请人： Vincent C. Martling , Zhenhua Xiao
发明人： Vincent C. Martling , Zhenhua Xiao
IPC分类号： F02C3/14 , F02C7/18
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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