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71. 发明授权

US07101150B2 Fastened vane assembly 有权
标题翻译：紧固叶片总成
公开(公告)号：US07101150B2
公开(公告)日：2006-09-05
申请号：US10842976
申请日：2004-05-11
申请人： Gary Bash , J. Page Strohl
发明人： Gary Bash , J. Page Strohl
IPC分类号： F01D1/02 , F01D9/00
CPC分类号： F01D9/042 , F05D2230/642 , F05D2240/80 , F05D2260/30
摘要： A vane assembly for a gas turbine is described wherein the vane assembly comprises a first vane and a second vane connected together by a plurality of flanges, at least one fastener, and at least one spring plate. The fastener and hole diameters in the respective flanges are sized such that the first vane and second vane are essentially pinned together along their inner flanges and allowed to adjust due to thermal growth along their outer flanges, while maintaining a constant seal along both inner and outer platform edges. The thermal growth along the outer flanges is made possible by oversized flange holes relative to the diameter of the fastener.
摘要翻译：描述了一种用于燃气轮机的叶片组件，其中叶片组件包括通过多个凸缘，至少一个紧固件和至少一个弹簧板连接在一起的第一叶片和第二叶片。相应凸缘中的紧固件和孔直径的尺寸使得第一叶片和第二叶片沿着其内凸缘基本上被固定在一起，并且由于沿着它们的外凸缘的热生长而允许调节，同时沿着内外两者保持恒定的密封平台边缘。通过相对于紧固件的直径的超大的凸缘孔，沿着外凸缘的热生长成为可能。

72. 发明申请

US20060168966A1 Self-Purging Pilot Fuel Injection System 有权
标题翻译：自清洗先导燃油喷射系统
公开(公告)号：US20060168966A1
公开(公告)日：2006-08-03
申请号：US10906057
申请日：2005-02-01
申请人： Peter Stuttaford , Stephen Jennings
发明人： Peter Stuttaford , Stephen Jennings
IPC分类号： F02C7/22
CPC分类号： F23R3/343 , F02C7/22 , F05D2260/60 , F23D2209/30
摘要： A gas turbine combustor having a self-purging pilot fuel injection system and method of operation thereof is disclosed. The pilot fuel injection system comprises a radial inflow swirler, a generally axially extending centerbody, and at least one fuel injection source. In operation a fluid containing at least air passes along the centerbody outer surface clearing any remaining fuel from proximate the fuel injection source so as to prevent flame attachment proximate the fuel injection source.
摘要翻译：公开了一种具有自净化引燃燃料喷射系统及其操作方法的燃气轮机燃烧器。引燃燃料喷射系统包括径向流入旋流器，大致轴向延伸的中心体和至少一个燃料喷射源。在操作中，至少含有空气的流体沿着中心体外表面通过，从燃料喷射源的附近清除任何剩余的燃料，以便防止燃料喷射源附近的火焰附着。

73. 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

74. 发明授权

US06935116B2 Flamesheet combustor 有权
标题翻译：火焰燃烧器
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
IPC分类号： F23R3/14 , F23R3/28 , F23R3/34 , F02C3/00 , F02C7/22 , F23R3/54
CPC分类号： F23R3/34 , F23R3/14 , F23R3/286
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。

75. 发明授权

US06865892B2 Combustion chamber/venturi configuration and assembly method 有权
标题翻译：燃烧室/文丘里配置和装配方法
公开(公告)号：US06865892B2
公开(公告)日：2005-03-15
申请号：US10248079
申请日：2002-12-17
申请人： Miguel Garrido , Shawn Miller
发明人： Miguel Garrido , Shawn Miller
IPC分类号： F23R3/00 , F23R3/60 , F02C7/20
CPC分类号： F23R3/60 , F23R3/005 , F23R2900/00017
摘要： A two-stage gas turbine combustor is disclosed that incorporates an improved assembly and disassembly methodology that results in improved inspection and repair techniques. The combustor includes an upper liner, lower liner, cap assembly, and a venturi assembly that directs cooling air into the combustion chamber for use in the combustion process, wherein a venturi assembly is inserted within an upper liner and an upper liner is then inserted in a lower liner. The venturi assembly, upper liner, and lower liner are fixed together with a plurality of easily removable retaining pins. The improved assembly allows for easier inspection and repair of the upper liner, lower liner, and venturi assembly.
摘要翻译：公开了一种两级燃气轮机燃烧器，其包括改进的组装和拆卸方法，其导致改进的检查和修复技术。燃烧器包括上衬套，下衬套，盖组件和文丘里组件，其将冷却空气引导到燃烧室中以用于燃烧过程，其中文丘里组件插入上衬垫内，然后将上衬管插入下层衬里文丘里组件，上衬套和下衬套与多个容易拆卸的保持销固定在一起。改进的组件允许更容易地检查和修理上衬套，下衬套和文氏管组件。

76. 发明申请

US20040031271A1 Convoluted seal with enhanced wear capability 有权
标题翻译：卷曲密封具有增强的磨损能力
公开(公告)号：US20040031271A1
公开(公告)日：2004-02-19
申请号：US10350757
申请日：2003-01-24
申请人： Power Systems Mfg, LLC
发明人： Stephen Jorgensen
IPC分类号： F23R003/42
CPC分类号： F01D9/023 , F01D11/005 , F02C7/20 , F05D2240/55 , F16J15/0806 , F16J15/0887
摘要： An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform. A second alternate embodiment is disclosed that utilizes a protective wear strip on the sealing device in lieu of coatings to provide a more effective wear reduction device between the sealing device and a turbine vane platform and transition duct aft frame.
摘要翻译：公开了一种用于过渡管道后部框架和涡轮机入口之间的改进的密封装置。改进的密封装置包括多个波纹金属密封件，其沿着后框架的弧形部分固定到过渡管道后部框架。波纹密封件接触过渡管道后部框架和涡轮机入口以提供更有效的密封并且控制引入以冷却涡轮叶片平台的压缩机排出空气的量。在优选实施例中，波纹状密封件被涂覆以减少磨损，磨损和磨损，并且与过渡管道热释放后框架和枢转轴承安装系统结合使用。还公开了密封件的替代实施例，其利用替代的冷却孔图案来向涡轮叶片平台提供额外的冷却空气。公开了第二替代实施例，其利用密封装置上的保护性耐磨条来代替涂层，以在密封装置与涡轮叶片平台和过渡管后架之间提供更有效的磨损减少装置。

77. 发明申请

US20030233832A1 Advanced cooling configuration for a low emissions combustor venturi 有权
标题翻译：用于低排放燃烧器文丘里管的先进冷却配置
公开(公告)号：US20030233832A1
公开(公告)日：2003-12-25
申请号：US10295437
申请日：2002-11-15
申请人： Power Systems Mfg, LLC
发明人： Vincent C. Martling , Zhenhua Xiao
IPC分类号： F23R003/30
CPC分类号： F23R3/005 , F23R3/06 , F23R3/286
摘要： A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process. In an alternate embodiment, a venturi is disclosed that incorporates a cooling passageway have a region of reduced area proximate a venturi throat region. The reduced area in conjunction with a plurality of raised ridges, located along the cooling passageway, for disturbing the cooling flow, enhance overall cooling effectiveness and improve venturi throat heat transfer.
摘要翻译：一种用于在燃气涡轮发动机中使用的低NOx排放燃烧器中的文丘里管和燃烧室的冷却空气的方法，该方法包括以下步骤：提供围绕所述燃烧室和文丘里管的环形空气通道，其中所述压力下的冷却空气进入在燃烧室的后部附近的燃烧室/文丘里管，沿着燃烧室使空气通过文丘里管，其中空气在文丘里管的会聚区域的前部附近离开。该方法防止任何通道/通道冷却空气被接收到燃烧室中，并且同时在空气已经经过文丘里管的燃烧室并且被加热之后引入冷却空气的出口从而提高了燃烧器的效率，同时降低和降低了燃烧过程中的NOx排放。在替代实施例中，公开了一种文丘里管，其包括冷却通道，其具有靠近文丘里喉部区域的减小区域。结合沿着冷却通道设置的用于干扰冷却流动的多个凸脊的减小面积增强了总体冷却效果并改善了文丘里管喉传热。

78. 发明公开

US20230193839A1 METHODS AND SYSTEMS FOR EXTENDING AN OPERATING WINDOW OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20230193839A1
公开(公告)日：2023-06-22
申请号：US17554398
申请日：2021-12-17
申请人： Power Systems Mfg., LLC
发明人： Wenping Wang , Danny Grobbe , Matthew Yaquinto , Jaime Serrano , Franklin van den Hout , Nicolas Demougeot
IPC分类号： F02C9/52
CPC分类号： F02C9/52 , F05D2220/32 , F05D2270/05 , F05D2270/303 , F05D2270/44
摘要： A method for extending an operating window of an operating mode of a gas turbine engine includes monitoring operating conditions of the gas turbine engine. The gas turbine engine is prevented by the method from transitioning from the first operating mode up to a second operating mode. A bulk temperature demand of the gas turbine engine is adjusted by a predefined amount to generate a first biased bulk temperature demand. The adjustment includes applying a first incremental bias to a bulk flame temperature schedule. The operation of the gas turbine engine is then adjusted based on the first biased bulk temperature demand. The monitored operating conditions are analyzed to determine whether one of the operating conditions has reached a threshold value.

79. 发明申请

US20060182622A1 Shroud Block with Enhanced Cooling 有权
标题翻译：带增强冷却的护罩块
公开(公告)号：US20060182622A1
公开(公告)日：2006-08-17
申请号：US10906377
申请日：2005-02-17
申请人： David Parker , Robert Moore , Charles Ellis
发明人： David Parker , Robert Moore , Charles Ellis
IPC分类号： F04D31/00
CPC分类号： F01D11/24 , F01D11/08 , F05D2240/11 , F05D2260/201
摘要： A shroud for surrounding a portion of a turbine flow path having improved cooling and durability is disclosed. The shroud includes a plurality of generally axial cooling holes spaced a substantially equal distance apart and a plurality of generally circumferential cooling holes oriented generally perpendicular to the generally axial cooling holes. The generally circumferentially cooling holes are spaced a non-uniform distance apart so as to provide cooling to selected portions of shroud sidewalls to lower shroud operating temperatures and improve shroud durability.
摘要翻译：公开了一种用于围绕具有改善的冷却和耐久性的涡轮流动路径的一部分的护罩。护罩包括间隔开大致相等的距离的多个大致轴向的冷却孔以及大致垂直于大致轴向的冷却孔定向的多个大致圆周的冷却孔。通常沿周向冷却孔间隔开不均匀的距离，以便为护罩侧壁的选定部分提供冷却，以降低护罩工作温度并改善护罩耐久性。

80. 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。

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