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51. 发明申请

US20120207953A1 COMPONENTS WITH COOLING CHANNELS AND METHODS OF MANUFACTURE 有权
标题翻译：具有冷却通道的组件和制造方法
公开(公告)号：US20120207953A1
公开(公告)日：2012-08-16
申请号：US13026595
申请日：2011-02-14
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： B32B3/30 , B32B1/02 , B23P17/04 , B05D3/12
CPC分类号： F01D5/147 , F01D5/186 , F05B2230/10 , F05B2230/30 , F05B2230/90 , Y02T50/67 , Y02T50/672 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49982 , Y10T428/13 , Y10T428/2457 , Y10T428/24612
摘要： A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.
摘要翻译：提供了一种制造组件的方法。该方法包括在衬底的外表面中形成一个或多个凹槽。每个凹槽至少部分地沿着基底的表面延伸并且具有基部，顶部和至少一个放电点。该方法还包括形成与每个凹槽相邻的排出点的偏移区域，并在衬底的表面的至少一部分上设置涂层。凹槽和涂层限定了一个或多个通道用于冷却部件。还提供带冷却通道的部件。

52. 发明申请

US20120154570A1 Thermal Inspection and Machining Systems and Methods of Use 有权
标题翻译：热检查和加工系统及使用方法
公开(公告)号：US20120154570A1
公开(公告)日：2012-06-21
申请号：US12968308
申请日：2010-12-15
申请人： Ronald Scott Bunker , Jason Randolph Allen , Jared Crosby
发明人： Ronald Scott Bunker , Jason Randolph Allen , Jared Crosby
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。

53. 发明申请

US20120151935A1 GAS TURBINE ENGINE AND METHOD OF OPERATING THEREOF 审中-公开
标题翻译：气体涡轮发动机及其运行方法
公开(公告)号：US20120151935A1
公开(公告)日：2012-06-21
申请号：US12971097
申请日：2010-12-17
申请人： Ronald Scott Bunker , Andrei Tristan Evulet
发明人： Ronald Scott Bunker , Andrei Tristan Evulet
IPC分类号： F02C6/00 , F02C7/08
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。

54. 发明申请

US20110219776A1 AERODYNAMIC FLAME STABILIZER 审中-公开
标题翻译：航空火焰稳定器
公开(公告)号：US20110219776A1
公开(公告)日：2011-09-15
申请号：US12724366
申请日：2010-03-15
申请人： Ronald Scott Bunker , Andrei Tristan Evulet
发明人： Ronald Scott Bunker , Andrei Tristan Evulet
IPC分类号： F23R3/18 , F02C7/22 , F02C3/14
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。

55. 发明授权

US07909507B2 Thermal inspection system and method 失效
标题翻译：热检查系统及方法
公开(公告)号：US07909507B2
公开(公告)日：2011-03-22
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： G01N25/00 , G01J5/00 , 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。

56. 发明授权

US07832212B2 High expansion fuel injection slot jet and method for enhancing mixing in premixing devices 有权
标题翻译：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
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23D14/62 , F23R3/286
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。

57. 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。

58. 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。

59. 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。

60. 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。

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