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51. 发明申请

US20090255332A1 THERMAL INSPECTION SYSTEM AND METHOD 失效
标题翻译：热检查系统和方法
公开(公告)号：US20090255332A1
公开(公告)日：2009-10-15
申请号：US12101285
申请日：2008-04-11
申请人： Ronald Scott Bunker , Nirm Velumylum Nirmalan
发明人： Ronald Scott Bunker , Nirm Velumylum Nirmalan
IPC分类号： G01F1/68 , G01K13/00
CPC分类号： G01K17/00 , G01F1/68 , G01K17/20
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。

52. 发明申请

US20090087312A1 Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method 有权
标题翻译：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
申请人： Ronald Scott Bunker , Gary Michael Itzel
发明人： Ronald Scott Bunker , Gary Michael Itzel
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。

53. 发明申请

US20080135530A1 METHOD OF MODIFYING THE END WALL CONTOUR IN A TURBINE USING LASER CONSOLIDATION AND THE TURBINES DERIVED THEREFROM 有权
标题翻译：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
申请人： Ching-Pang Lee , Hsin-Pang Wang , Ronald Scott Bunker , Sudhir Kumar Tewari , Magdi Naim Azer
发明人： Ching-Pang Lee , Hsin-Pang Wang , Ronald Scott Bunker , Sudhir Kumar Tewari , Magdi Naim Azer
IPC分类号： B23K26/20 , B23P15/02
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。

54. 发明申请

US20080057271A1 Film cooled slotted wall and method of making the same 有权
标题翻译：薄膜开槽壁及其制作方法
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。

55. 发明授权

US07182576B2 Hot gas path component with mesh and impingement cooling 失效
标题翻译：热气路组件，带网孔和冲击冷却
公开(公告)号：US07182576B2
公开(公告)日：2007-02-27
申请号：US10881506
申请日：2004-06-29
申请人： Ronald Scott Bunker , Ching-Pang Lee
发明人： Ronald Scott Bunker , Ching-Pang Lee
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。

56. 发明授权

US06984100B2 Component and turbine assembly with film cooling 失效
标题翻译：组件和汽轮机组件与薄膜冷却
公开(公告)号：US06984100B2
公开(公告)日：2006-01-10
申请号：US10611749
申请日：2003-06-30
申请人： Ronald Scott Bunker , Canan Uslu Hardwicke
发明人： Ronald Scott Bunker , Canan Uslu Hardwicke
IPC分类号： F01D5/14
CPC分类号： F01D5/186 , F05D2230/232 , F05D2230/312 , F05D2230/314 , F05D2250/11 , F05D2250/13 , F05D2260/221 , F05D2260/2212 , F05D2260/22141 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A component includes a wall with a cold and a hot surface. At least one film-cooling hole extends through the wall for flowing a coolant from the cold to the hot surface. The film-cooling hole defines an exit site in the hot surface. At least one flow modifier is formed on the hot surface and is adapted to direct the coolant flowing from the film-cooling hole and out of the exit site toward the hot surface. The flow modifier extends outwards from and conforms to the hot surface. A turbine assembly includes a first and a second component that define a secondary cooling slot, which receives and guides a secondary coolant flow. At least one flow modifier is formed on a surface of one of the two components and is adapted to enhance the secondary coolant flow along at least one of the two components within the secondary coolant slot.
摘要翻译：组件包括具有冷和热表面的壁。至少一个薄膜冷却孔延伸穿过壁，用于使冷却剂从冷的表面流到热表面。薄膜冷却孔在热表面中限定出口部位。在热表面上形成至少一个流动改性剂，并适于将从薄膜冷却孔流出的冷却剂引导到离开出口部位的冷却表面。流动调节器向外延伸并符合热表面。涡轮机组件包括限定二次冷却槽的第一和第二部件，其接收和引导二次冷却剂流。在两个部件中的一个部件的表面上形成至少一个流动调节器，并且适于增强沿次级冷却剂槽内的两个部件中的至少一个的二次冷却剂流。

57. 发明授权

US06978621B2 Turbo recuperator device 失效
标题翻译：涡轮换热装置
公开(公告)号：US06978621B2
公开(公告)日：2005-12-27
申请号：US10331342
申请日：2002-12-31
申请人： Ronald Scott Bunker , Chellappa Balan
发明人： Ronald Scott Bunker , Chellappa Balan
IPC分类号： F01D13/02 , F02C3/04 , F02C6/08 , F02C6/18 , F02C7/12 , F02C7/18
CPC分类号： F02C6/08 , F01D13/02 , F02C3/04 , F02C6/18 , F02C7/12 , F02C7/18 , F05D2260/205
摘要： A device and method for recuperating a gas turbine engine comprises a compressor being configured to receive a coolant fluid stream, to compress the coolant fluid stream and to discharge the compressed coolant fluid stream to a turbine in fluid communication with the compressor. The compressed coolant fluid stream undergoing thermal exchange within the turbine, exit the turbine thereafter. A source of a working fluid stream is in fluid communication with the turbine. The working fluid stream is fluidly isolated from a portion of the coolant fluid stream and undergoing thermodynamic expansion through the turbine to extract energy therefrom. Where desired, the entire coolant fluid stream is fluidly isolated from the working fluid stream. At least a portion of the coolant fluid stream is channeled downstream of the turbine to supply a preheated process fluid stream to an adjacent system.
摘要翻译：一种用于回收燃气涡轮发动机的装置和方法，包括压缩机，其构造成接收冷却剂流体流，以压缩冷却剂流体流并将压缩的冷却剂流体流排放到与压缩机流体连通的涡轮机。在涡轮机内进行热交换的压缩的冷却剂流体流随后离开涡轮机。工作流体流的源与涡轮流体连通。工作流体流与冷却剂流体流的一部分流体隔离，并通过涡轮进行热力学膨胀，以从其中提取能量。如果需要，整个冷却剂流体流与工作流体流流体隔离。冷却剂流体流的至少一部分被引导到涡轮机的下游，以向相邻的系统提供预热的过程流体流。

58. 发明授权

US06953633B2 Fiber cooling of fuel cells 失效
标题翻译：燃料电池的光纤冷却
公开(公告)号：US06953633B2
公开(公告)日：2005-10-11
申请号：US10212541
申请日：2002-08-06
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： H01M8/02 , H01M8/00 , H01M8/04 , H01M8/08 , H01M8/10 , H01M8/12 , H01M8/24
CPC分类号： H01M8/2432 , H01M8/0258 , H01M8/026 , H01M8/04089 , H01M8/241 , H01M8/243
摘要： Fuel cells for example solid oxide fuel cells require cooling to maintain temperature levels and remove thermal energy generated by the fuel cells. The present invention provides a fuel cell assembly comprising at least one fuel cell. The fuel cell comprises an anode, a cathode, an electrolyte interposed therebetween, an interconnect which is in intimate contact with at least one of the anode, the cathode and the electrolyte; at least one fluid flow channel which is disposed within the fuel cell, and at least one fiber which is disposed within the fluid flow channel. The fiber disposed within the fluid flow channel disrupts a fluid flow during travel of the fluid within the fluid flow channel to generate unsteady wakes. These unsteady wakes enhance the local heat transfer characteristics adjacent to at least one fiber. A higher Reynolds number enhances the heat transfer characteristics proportionately. Enhanced heat transfer characteristics increase the ability to remove heat more efficiently and more effectively.
摘要翻译：燃料电池例如固体氧化物燃料电池需要冷却以维持温度水平并消除由燃料电池产生的热能。本发明提供一种包括至少一个燃料电池的燃料电池组件。燃料电池包括阳极，阴极，介于其间的电解质，与阳极，阴极和电解质中的至少一个紧密接触的互连; 布置在燃料电池内的至少一个流体流动通道和设置在流体流动通道内的至少一个纤维。布置在流体流动通道内的纤维在流体流动通道内的流体行进期间破坏流体流动，以产生不稳定的唤醒。这些不稳定的醒来增强了与至少一根纤维相邻的局部传热特性。雷诺数越高，按比例提高传热特性。增强的传热特性增加了更有效和更有效地去除热量的能力。

59. 发明授权

US06722134B2 Linear surface concavity enhancement 有权
标题翻译：线性表面凹凸增强
公开(公告)号：US06722134B2
公开(公告)日：2004-04-20
申请号：US10065115
申请日：2002-09-18
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F02C718
CPC分类号： F01D5/286 , F05D2250/60 , F05D2250/712 , F05D2260/2212 , F05D2260/2214 , F05D2300/501
摘要： A turbine component having a surface provided with a heat transfer enhancement feature formed therein that includes at least one linear surface concavity comprised of plural overlapped surface concavities.
摘要翻译：一种具有形成有传热增强特征的表面的涡轮机部件，其包括由多个重叠表面凹部组成的至少一个线性表面凹部。

60. 发明授权

US06494678B1 Film cooled blade tip 有权
标题翻译：薄膜冷却叶片尖端
公开(公告)号：US06494678B1
公开(公告)日：2002-12-17
申请号：US09681744
申请日：2001-05-31
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/18
摘要： A turbine assembly having at least one rotor blade comprises an airfoil having a pressure sidewall, a suction sidewall and a tip portion having a tip cap. A tip is disposed on the tip cap. A plurality of blade tip cooling holes are positioned within the airfoil near the tip portion. Cooling grooves are disposed within the airfoil to connect the blade tip cooling holes with the top portion of the tip to transition cooling flow from the cooling holes to the tip portion.
摘要翻译：具有至少一个转子叶片的涡轮机组件包括具有压力侧壁的翼型件，抽吸侧壁和具有尖端盖的尖端部分。尖端设置在尖端盖上。多个叶片尖端冷却孔位于靠近顶端部分的翼型内。冷却槽设置在翼型件内，以将叶片尖端冷却孔与顶端的顶部连接，以过渡从冷却孔到顶端部分的冷却流。

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