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公开(公告)号：US20120154570A1
公开(公告)日：2012-06-21
申请号：US12968308
申请日：2010-12-15
IPC分类号： H04N7/18
CPC分类号： F01D5/005 , B23P2700/06 , F01D5/14 , F01D25/285 , F05D2260/80 , G01N21/951 , G01N25/18 , G01N25/72
摘要： The present application provides a thermal imaging and machining system for a machine component. The thermal imaging and machining system may include a machining subsystem with a machining device for drilling one or more holes in the machine component and a thermal inspection subsystem positioned about the machining subsystem. The thermal inspection subsystem may include an imager and one or more fluid supply lines such that a thermal response of the holes in the machine component may be determined.
摘要翻译： 本申请提供了用于机器部件的热成像和加工系统。 热成像和加工系统可以包括具有用于在机器部件中钻一个或多个孔的加工装置的加工子系统以及围绕加工子系统定位的热检查子系统。 热检查子系统可以包括成像器和一个或多个流体供应管线，使得可以确定机器部件中的孔的热响应。
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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：US07909507B2
公开(公告)日：2011-03-22
申请号：US12101285
申请日：2008-04-11
摘要： A thermal inspection method is provided for a component comprising at least one complex internal passage arrangement defining at least one opening. The thermal inspection method includes flowing a fluid through the at least one complex internal passage arrangement. The fluid has an initial temperature that differs from an initial temperature of the component. The thermal inspection method further includes measuring a thermal response of the component to the fluid flow and analyzing the thermal response to determine a number of heat transfer coefficients {hlmn} corresponding to respective locations {l,m,n} within the complex internal passage arrangement. The thermal inspection method further includes using the heat transfer coefficients {hlmn} to determine at least one of (a) a flow rate through respective ones of the at least one opening, and (b) a cross-sectional area for respective ones of the at least one opening.
摘要翻译： 为包括限定至少一个开口的至少一个复杂内部通道装置的部件提供热检查方法。 热检查方法包括使流体流过至少一个复合内部通道装置。 流体具有不同于组件的初始温度的初始温度。 热检测方法还包括测量部件对流体流的热响应并分析热响应以确定与复合内通道装置内的各个位置{1，m，n}对应的多个传热系数{hlmn} 。 热检测方法还包括使用传热系数（hlmn）来确定（a）通过至少一个开口中的相应的一个开口的流量中的至少一个，和（b）相应的一个开口的横截面积 至少一个开口。
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85.发明授权High expansion fuel injection slot jet and method for enhancing mixing in premixing devices 有权高膨胀燃料喷射槽喷射和预混合装置中混合增强的方法公开(公告)号：US07832212B2
公开(公告)日：2010-11-16
申请号：US11558760
申请日：2006-11-10
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
摘要： A premixing device includes an air inlet, at least one fuel inlet slot having a wall profile configured to form a fuel boundary layer along a portion of a wall of the premixing device, a mixing chamber, and at least one diverging fuel injection slot jet disposed inside the at least one fuel inlet slot, the slot jet being configured to create a flow separation region in a diverging portion thereof to generate mixing turbulence at an outlet of the slot jet to aerodynamically enhance a mixing of the fuel from the boundary layer with compressed air without causing a boundary layer flow separation and a flame holding in the mixing chamber. Low-emission combustors, gas turbine combustors, methods for premixing a fuel and an oxidizer in a combustion system, a gas turbine, and a gas to liquid system using the premixing device are also disclosed.
摘要翻译： 预混合装置包括空气入口，至少一个燃料入口狭槽，其具有被配置为沿着预混合装置的壁的一部分形成燃料边界层的壁轮廓，混合室以及至少一个发散燃料喷射槽射流 在所述至少一个燃料入口狭槽内部，所述狭槽射流被配置为在其发散部分中产生流动分离区域，以在所述狭槽射流的出口处产生混合湍流，以空气动力学地增强来自边界层的燃料与压缩的混合 空气，而不会在混合室中引起边界层流动分离和火焰保持。 还公开了低排放燃烧器，燃气轮机燃烧器，用于将燃料和氧化剂在燃烧系统中预混合的方法，燃气轮机以及使用该预混合装置的气体与液体系统。
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公开(公告)号：US20090255332A1
公开(公告)日：2009-10-15
申请号：US12101285
申请日：2008-04-11
摘要： A thermal inspection method is provided for a component comprising at least one complex internal passage arrangement defining at least one opening. The thermal inspection method includes flowing a fluid through the at least one complex internal passage arrangement. The fluid has an initial temperature that differs from an initial temperature of the component. The thermal inspection method further includes measuring a thermal response of the component to the fluid flow and analyzing the thermal response to determine a number of heat transfer coefficients {hlmn} corresponding to respective locations {l,m,n} within the complex internal passage arrangement. The thermal inspection method further includes using the heat transfer coefficients {hlmn} to determine at least one of (a) a flow rate through respective ones of the at least one opening, and (b) a cross-sectional area for respective ones of the at least one opening.
摘要翻译： 为包括限定至少一个开口的至少一个复杂内部通道装置的部件提供热检查方法。 热检查方法包括使流体流过至少一个复杂的内部通道装置。 流体具有不同于组件的初始温度的初始温度。 热检测方法还包括测量部件对流体流的热响应并分析热响应以确定与复合内通道装置内的各个位置{1，m，n}对应的多个传热系数{hlmn} 。 热检测方法还包括使用传热系数（hlmn）来确定（a）通过至少一个开口中的相应的一个开口的流量中的至少一个，和（b）相应的一个开口的横截面积 至少一个开口。
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87.发明申请Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method 有权涡轮机翼冷却通道采用双旋流动机理和方法公开(公告)号：US20090087312A1
公开(公告)日：2009-04-02
申请号：US11863744
申请日：2007-09-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译： 涡轮机翼片包括具有凹形冷却流道的前缘。 凹形冷却流道的顶点将流动通道分成相邻的区域。 涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。 第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。
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88.发明申请METHOD OF MODIFYING THE END WALL CONTOUR IN A TURBINE USING LASER CONSOLIDATION AND THE TURBINES DERIVED THEREFROM 有权使用激光合成技术在涡轮机中修复端壁轮廓的方法及其衍生的涡轮机公开(公告)号：US20080135530A1
公开(公告)日：2008-06-12
申请号：US11609150
申请日：2006-12-11
CPC分类号： F01D5/145 , B22F3/1055 , B22F5/009 , B22F5/04 , C23C24/10 , C23C26/02 , F05D2230/234 , F05D2230/30 , F05D2230/50 , F05D2270/17 , Y02P10/295 , Y10T29/49238 , Y10T29/49318 , Y10T29/49336 , Y10T29/49337 , Y10T29/49746
摘要： Disclosed herein is a method comprising creating a weld pool using a laser; wherein the weld pool is created on a part of a turbine; and wherein the weld pool comprises molten metal or ceramic derived as a result of a heat interaction between the laser and the part of the turbine; adding a metal or a ceramic powder or a wire filler to the melt pool; and modifying the part of the turbine in a manner that results in a change of about 0.005 to about 50 volume percent in the part of the turbine, while improving the aerodynamic efficiency of the turbine in an amount of about 0.1 to about 5 percent over a corresponding unmodified turbine.
摘要翻译： 本文公开了一种包括使用激光产生熔池的方法; 其中所述熔池在涡轮机的一部分上产生; 并且其中所述熔池包括由于所述激光器和所述涡轮机的所述部分之间的热相互作用而导出的熔融金属或陶瓷; 在熔池中加入金属或陶瓷粉末或丝线填料; 并且以在涡轮机部分中导致约0.005至约50体积％的变化的方式修改涡轮机的一部分，同时以相对于涡轮机的大约0.1％至大约5％的量改进涡轮机的空气动力学效率 相应的未修改的涡轮机。
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公开(公告)号：US20080057271A1
公开(公告)日：2008-03-06
申请号：US11511840
申请日：2006-08-29
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： B32B3/10
CPC分类号： F01D5/186 , F05D2260/202 , Y10T428/24273 , Y10T428/24298 , Y10T428/24322
摘要： An article includes a substrate having a first surface and a second surface; a slot disposed in the second surface, the slot having a bottom surface substantially parallel to the second surface, a first sidewall, and a second sidewall, wherein the first sidewall is substantially perpendicular to the second surface and wherein the first sidewall includes a plurality of beveled edge portions in physical communication with the second surface and the bottom surface; and a plurality of passage holes extending through the substrate from the first surface to the bottom surface, wherein the plurality of passage holes are aligned within the slot such that at least one beveled edge portion is disposed between two passage holes.
摘要翻译： 一种制品包括具有第一表面和第二表面的基底; 设置在所述第二表面中的槽，所述槽具有基本上平行于所述第二表面的底表面，第一侧壁和第二侧壁，其中所述第一侧壁基本上垂直于所述第二表面，并且其中所述第一侧壁包括多个 与第二表面和底表面物理连通的斜边缘部分; 以及多个通孔，从所述第一表面延伸到所述底表面，其中所述多个通孔在所述槽内对齐，使得至少一个倾斜边缘部分设置在两个通孔之间。
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公开(公告)号：US07182576B2
公开(公告)日：2007-02-27
申请号：US10881506
申请日：2004-06-29
IPC分类号： F01D5/18
CPC分类号： F28F13/12 , F01D5/187 , F05D2230/90 , F05D2250/28 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F28F3/022 , F28F3/044 , Y02T50/67 , Y02T50/671 , Y02T50/676 , Y10T29/4932
摘要： A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions. The pins define a mesh cooling arrangement with a number of flow channels. The inner portion of the wall defines a number of dimples. A method for forming a number of cooling holes in a component is described. The component has at least one wall with inner and outer portions. The inner portion defines a number of dimples. The method includes centering a drilling tool on a dimple, drilling at least one impingement cooling hole through the inner portion of the wall at the dimple using the drilling tool, and repeating the centering and drilling steps for a number of dimples to drill a number of impingement cooling holes in the inner portion of the wall.
摘要翻译： 一个部件包括至少一个具有内部部分和外部部分的壁。 多个销在内部和外部之间延伸。 销钉定义了具有多个流动通道的网状冷却装置。 壁的内部部分限定了多个凹坑。 描述了在部件中形成多个冷却孔的方法。 该部件具有至少一个具有内部和外部部分的壁。 内部部分限定了一些凹坑。 该方法包括将钻孔工具定中在凹坑上，使用钻孔工具在凹坑处穿过壁的内部部分的至少一个冲击冷却孔钻孔，并重复多个凹坑的定中心和钻孔步骤以钻出若干个 在壁的内部的冲击冷却孔。
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