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公开(公告)号：US08899494B2
公开(公告)日：2014-12-02
申请号：US13077719
申请日：2011-03-31
CPC分类号： F23R3/30 , F23C2900/07001 , F23D2209/10 , F23R3/14 , F23R3/286 , F23R2900/00014 , F23R2900/03281
摘要： In certain embodiments, a fuel injector includes a wall separating a fuel passage from an air passage. The fuel injector also includes a fuel injection port extending from a first side of the wall to a second side of the wall for injecting a flow of fuel from the fuel passage into a flow of air in the air passage. In addition, the fuel injector includes first and second feedback lines extending from a downstream end of the fuel injection port to an upstream end of the fuel injection port. The first and second feedback lines are disposed on opposite sides of the fuel injection port. In addition, the first and second feedback lines are disposed entirely within the wall.
摘要翻译： 在某些实施例中，燃料喷射器包括将燃料通道与空气通道分开的壁。 燃料喷射器还包括从壁的第一侧延伸到壁的第二侧的燃料喷射端口，用于将燃料流从燃料通道喷射到空气通道中的空气流中。 另外，燃料喷射器包括从燃料喷射口的下游端延伸到燃料喷射口的上游端的第一和第二反馈线。 第一和第二反馈线设置在燃料喷射口的相对侧上。 此外，第一和第二反馈线完全设置在壁内。
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公开(公告)号：US20120248217A1
公开(公告)日：2012-10-04
申请号：US13077719
申请日：2011-03-31
IPC分类号： F02D1/00
CPC分类号： F23R3/30 , F23C2900/07001 , F23D2209/10 , F23R3/14 , F23R3/286 , F23R2900/00014 , F23R2900/03281
摘要： In certain embodiments, a fuel injector includes a wall separating a fuel passage from an air passage. The fuel injector also includes a fuel injection port extending from a first side of the wall to a second side of the wall for injecting a flow of fuel from the fuel passage into a flow of air in the air passage. In addition, the fuel injector includes first and second feedback lines extending from a downstream end of the fuel injection port to an upstream end of the fuel injection port. The first and second feedback lines are disposed on opposite sides of the fuel injection port. In addition, the first and second feedback lines are disposed entirely within the wall.
摘要翻译： 在某些实施例中，燃料喷射器包括将燃料通道与空气通道分开的壁。 燃料喷射器还包括从壁的第一侧延伸到壁的第二侧的燃料喷射端口，用于将燃料流从燃料通道喷射到空气通道中的空气流中。 另外，燃料喷射器包括从燃料喷射口的下游端延伸到燃料喷射口的上游端的第一和第二反馈线。 第一和第二反馈线设置在燃料喷射口的相对侧上。 此外，第一和第二反馈线完全设置在壁内。
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3.发明申请GAS TURBINE GUIDE VANES WITH TANDEM AIRFOILS AND FUEL INJECTION AND METHOD OF USE 审中-公开气体涡轮引导件，带有标准气体和燃油喷射和使用方法公开(公告)号：US20080134685A1
公开(公告)日：2008-06-12
申请号：US11567796
申请日：2006-12-07
IPC分类号： F02C7/26
CPC分类号： F01D5/146 , F01D9/041 , F01D9/065 , F02K3/08 , F23C2900/07001 , F23R3/20 , Y02T50/673
摘要： Guide vanes include a first flange connected with a casing of a gas turbine engine, a second flange connected with the casing, a first airfoil disposed between the first and second flanges and connected thereto, and a second airfoil disposed between the first and second flanges and connected thereto so as to form a gap extending radially between a first trailing portion of the first airfoil and a second leading portion of the second airfoil, the hollow portion being in flow communication with the gap so as to allow a gaseous fuel to flow from the hollow portion through the gap and into a fluid flowing over the guide vane. Gas turbines that use the guide vanes and methods for injecting a gaseous fuel for combustion in a gas turbine engine are also disclosed.
摘要翻译： 引导叶片包括与燃气涡轮发动机的壳体连接的第一凸缘，与壳体连接的第二凸缘，设置在第一和第二凸缘之间并与之连接的第一翼型件，以及设置在第一和第二凸缘之间的第二翼型件， 连接到其上以形成在第一翼型件的第一尾部与第二翼型件的第二前导部之间径向延伸的间隙，中空部分与间隙流动连通，以允许气体燃料从 中空部分穿过间隙并流入流过导叶的流体。 还公开了使用引导叶片的燃气轮机和用于在燃气涡轮发动机中燃烧气体燃料的方法。
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公开(公告)号：US09284231B2
公开(公告)日：2016-03-15
申请号：US13328704
申请日：2011-12-16
CPC分类号： F02C7/16 , C04B41/0072 , C04B41/009 , C04B41/80 , F01D15/10 , F01D25/12 , F02C7/12 , F05D2260/232 , Y02T50/672 , Y02T50/676 , C04B35/56 , C04B35/565 , C04B35/806 , C04B41/4529
摘要： A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
摘要翻译： 公开了一种具有由高碳活性气体由烃提供的难熔碳化物的稳定化的涡轮发电系统。 本公开还包括使用高碳活性气体来稳定热气路径成分的方法。
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公开(公告)号：US20120151935A1
公开(公告)日：2012-06-21
申请号：US12971097
申请日：2010-12-17
CPC分类号： F23R3/005 , F02C3/10 , F02C6/003 , F02C9/52 , F02C9/54 , F02K3/11 , F23R3/06 , F23R3/16 , F23R2900/03042
摘要： A method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream and a second stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. The reheat combustor is cooled using the second stream of the expanded combustion gas.
摘要翻译： 用于操作燃气涡轮发动机的方法包括压缩压缩机中的空气流并且通过在燃烧器中燃烧从压缩机排出的压缩空气流而产生后燃气体。 后燃烧气体在第一涡轮机中膨胀。 从第一涡轮机排出的膨胀燃烧气体被分成第一流和第二流。 膨胀燃烧气体的第一流在再热燃烧器中燃烧。 使用膨胀燃烧气体的第二流冷却再热燃烧器。
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公开(公告)号：US20110219776A1
公开(公告)日：2011-09-15
申请号：US12724366
申请日：2010-03-15
CPC分类号： F23R3/20 , F23R3/346 , F23R2900/03341
摘要： A flame stabilizer is in fluid communication with a combustor of a gas turbine engine. The flame stabilizer has a body with an aerodynamic shape that creates a flow recirculation zone by injection of fluid through a plurality of holes in the body of the flame stabilizer. The aerodynamic shape of the body reduces pressure loss in the combustor, particularly when no fuel is being provided to the combustor. In addition, the magnitude of the flow recirculation zone can be modulated by selectively adjusting the flow rate of fluid through the holes, or by selectively adjusting the size of the holes.
摘要翻译： 火焰稳定器与燃气涡轮发动机的燃烧器流体连通。 火焰稳定器具有空气动力学形状的主体，其通过在火焰稳定器的主体中的多个孔注入流体而产生流动再循环区域。 主体的空气动力学形状减少了燃烧器中的压力损失，特别是当没有向燃烧器提供燃料时。 此外，可以通过选择性地调节通过孔的流体的流量，或者通过选择性地调整孔的尺寸来调节流动再循环区的大小。
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公开(公告)号：US09435208B2
公开(公告)日：2016-09-06
申请号：US13448469
申请日：2012-04-17
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
CPC分类号： F01D5/147 , B23P15/04 , F01D5/186 , F01D5/189 , F05D2230/30 , F05D2230/90 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y10T29/49229
摘要： A component includes a substrate having outer and inner surfaces, where the inner surface defines at least one hollow, interior space. The outer surface defines pressure side and suction side walls, which are joined together at leading and trailing edges of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface. The coating comprises at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge. A method of forming cooling channels in the vicinity of the trailing edge is also provided.
摘要翻译： 组件包括具有外表面和内表面的基底，其中内表面限定至少一个中空的内部空间。 外表面限定压力侧和吸力侧壁，其在部件的前缘和后缘处连接在一起。 外表面限定一个或多个凹槽，其至少部分地沿着后缘附近的压力或吸力侧壁延伸。 每个槽与相应的中空的内部空间流体连通。 该部件还包括设置在外部基板表面的至少一部分上的涂层。 该涂层包括至少一个在凹槽上延伸的结构涂层，使得凹槽和结构涂层一起限定一个或多个通道以冷却后缘。 还提供了在后缘附近形成冷却通道的方法。
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公开(公告)号：US09327384B2
公开(公告)日：2016-05-03
申请号：US13168117
申请日：2011-06-24
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
CPC分类号： B24C1/045 , C23C4/04 , C23C4/073 , F01D5/186 , F01D5/187 , F01D5/288 , F05D2230/90 , Y02T50/672 , Y02T50/676
摘要： A manufacturing method includes forming one or more grooves in a component that comprises a substrate with an outer surface. The substrate has at least one interior space, and each groove extends at least partially along the substrate and has a base. The manufacturing method further includes forming one or more access holes through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. The manufacturing method further includes forming at least one connecting groove in the component, such that each connecting groove intersects at least a subset of the one or more grooves. The manufacturing method further includes disposing a coating over at least a portion of the outer surface of the substrate, such that the groove(s) and the coating together define one or more channels for cooling the component. The coating does not completely bridge the connecting groove, such that the connecting groove at least partially defines an exit region for the respective cooling channel(s).
摘要翻译： 一种制造方法包括在包括具有外表面的基板的部件中形成一个或多个凹槽。 衬底具有至少一个内部空间，并且每个凹槽至少部分地沿衬底延伸并且具有基底。 制造方法还包括通过相应凹槽的底部形成一个或多个入口孔，以将凹槽与相应的中空内部空间流体连通。 制造方法还包括在部件中形成至少一个连接槽，使得每个连接槽与一个或多个槽的至少一个子集相交。 该制造方法还包括在衬底的外表面的至少一部分上设置涂层，使得凹槽和涂层一起限定一个或多个通道以冷却部件。 涂层不能完全桥接连接槽，使得连接槽至少部分地限定用于各个冷却通道的出口区域。
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9.发明授权Components with microchannel cooled platforms and fillets and methods of manufacture 有权具有微通道冷却平台和圆角的部件和制造方法公开(公告)号：US09243503B2
公开(公告)日：2016-01-26
申请号：US13478517
申请日：2012-05-23
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
CPC分类号： F01D5/187 , F01D5/288 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A component includes a substrate that has outer and inner surfaces. The inner surface defines at least one hollow, interior space. The outer surface defines pressure and suction sidewalls that are joined together at leading and trailing edges of the component and together form an airfoil portion of the component. The outer substrate surface further defines at least one platform and at least one fillet that extends between and integrally connects the airfoil to the respective platform. The outer surface defines one or more grooves that extend at least partially along a respective fillet. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface and including at least a structural coating that extends over the groove(s). The groove(s) and the structural coating together define channel(s) for cooling the respective fillet.
摘要翻译： 组件包括具有外表面和内表面的基底。 内表面限定至少一个中空的内部空间。 外表面限定压力和抽吸侧壁，其在部件的前缘和后缘处连接在一起并且一起形成部件的翼型部分。 外基材表面进一步限定至少一个平台和至少一个在所述翼型件之间延伸并且将翼片整体连接到相应的平台的圆角。 外表面限定了至少部分地沿着相应的圆角延伸的一个或多个凹槽。 每个槽与相应的中空的内部空间流体连通。 该部件还包括设置在外部基底表面的至少一部分上的涂层，并且至少包括在凹槽上延伸的结构涂层。 沟槽和结构涂层一起限定用于冷却相应圆角的通道。
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公开(公告)号：US09216491B2
公开(公告)日：2015-12-22
申请号：US13168144
申请日：2011-06-24
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
CPC分类号： B24C1/045 , B23K26/364 , B23K26/389 , B23K2101/001 , F01D5/186 , F05D2230/14 , F05D2230/90 , Y02T50/672 , Y02T50/676
摘要： A manufacturing method is provided. The manufacturing method includes forming one or more grooves in a component comprising a substrate. Each groove extends at least partially along the substrate and has a base, a top and at least one discharge end. The manufacturing method further includes forming a crater, such that the crater is in fluid connection with the respective discharge end for each groove, and disposing a coating over at least a portion of an outer surface of the substrate. The groove(s) and the coating together define one or more channels for cooling the component. The coating does not completely bridge each of the one or more craters, such that each crater defines a film exit. A component with cratered film exits is also provided.
摘要翻译： 提供了一种制造方法。 制造方法包括在包括基板的部件中形成一个或多个凹槽。 每个凹槽至少部分地沿着衬底延伸并且具有底座，顶部和至少一个排出端。 制造方法还包括形成火山口，使得所述火山口与每个槽的相应排出端流体连接，并且在所述基板的外表面的至少一部分上设置涂层。 凹槽和涂层一起限定一个或多个通道用于冷却部件。 涂层不完全桥接一个或多个凹坑中的每一个，使得每个凹坑限定薄膜出口。 还提供了带有起重胶卷出口的部件。
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