公开(公告)号：US07186084B2

公开(公告)日：2007-03-06

申请号：US10720045

申请日：2003-11-19

申请人： Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  Ching-Pang Lee

发明人： Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  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 of the wall. The pins define a mesh cooling arrangement having a number of flow channels. A number of dimples are located in at least one of the inner and outer portions of the wall. The component may also include a number of turbulators disposed on at least one of the inner and outer portions 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。 多个销在壁的内部和外部之间延伸。 销钉限定具有多个流动通道的网状冷却装置。 多个凹坑位于壁的内部和外部的至少一个中。 该部件还可以包括设置在壁的内部和外部部分中的至少一个上的多个紊流器。

公开(公告)号：US06981840B2

公开(公告)日：2006-01-03

申请号：US10692700

申请日：2003-10-24

申请人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Chander Prakash

发明人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Chander Prakash

IPC分类号： F03D11/00

CPC分类号： F01D5/187 ,  F05D2260/22141 ,  Y02T50/676

摘要： A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.

摘要翻译： 涡轮机翼片包括在前缘和后缘之间延伸并且在根部和尖端之间的跨度中的压力和抽吸侧壁。 隔膜间隔开在侧壁之间以在隔膜的相对侧上限定两个冷却回路，其在前缘和后缘之间会聚。 引脚阵列在电路的放电端从压力侧壁向内延伸，并且引脚的长度减小以符合会聚电路。

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。

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。

公开(公告)号：US20100282721A1

公开(公告)日：2010-11-11

申请号：US12435547

申请日：2009-05-05

申请人： Ronald Scott Bunker ,  Wenwu Zhang ,  Wilbur Douglas Scheidt ,  Magdi Naim Azer ,  Marshall Gordon Jones ,  Ching-Pang Lee

发明人： Ronald Scott Bunker ,  Wenwu Zhang ,  Wilbur Douglas Scheidt ,  Magdi Naim Azer ,  Marshall Gordon Jones ,  Ching-Pang Lee

IPC分类号： B23K26/38

CPC分类号： F01D25/12 ,  B23K26/0624 ,  B23K26/389 ,  F01D25/285 ,  F05D2230/13 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

摘要： A system for producing at least one trench to improve film cooling in a sample is provided. The system includes at least one laser source outputting at least one pulsed laser beam. The pulsed laser beam includes a pulse duration including a range less than about 50 μs, an energy per pulse having a range less than about 0.1 Joule, and a repetition rate with a range greater than about 1000 Hz. The system also includes a control subsystem coupled to the laser source, the control subsystem configured to synchronize a position of the sample with the pulse duration and energy level in order to selectively remove at least one of a thermal barrier coating, a bondcoat and a substrate metal in the sample to form the at least one trench.

摘要翻译： 提供一种用于生产至少一个沟槽以改善样品中的膜冷却的系统。 该系统包括输出至少一个脉冲激光束的至少一个激光源。 脉冲激光束包括包括小于约50μs的范围的脉冲持续时间，具有小于约0.1焦耳的范围的每脉冲的能量以及范围大于约1000Hz的重复率。 该系统还包括耦合到激光源的控制子系统，该控制子系统被配置为使样本的位置与脉冲持续时间和能量水平同步，以选择性地去除热障涂层，粘合涂层和基底中的至少一个 金属，以形成至少一个沟槽。

公开(公告)号：US07134842B2

公开(公告)日：2006-11-14

申请号：US11022121

申请日：2004-12-24

申请人： Anna Tam ,  Ching-Pang Lee ,  Kevin Richard Kirtley ,  Ronald Scott Bunker ,  Scott Henry Lamson ,  Scott Michael Carson

发明人： Anna Tam ,  Ching-Pang Lee ,  Kevin Richard Kirtley ,  Ronald Scott Bunker ,  Scott Henry Lamson ,  Scott Michael Carson

IPC分类号： F01D5/22

CPC分类号： F01D5/145 ,  F01D5/143 ,  F05D2240/80 ,  F05D2250/70 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

摘要： A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

摘要翻译： 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 每个平台具有扇形流动表面，包括邻近前缘的压力侧的凸起，以及与前缘的后侧的吸入侧邻接的碗。

公开(公告)号：US07011502B2

公开(公告)日：2006-03-14

申请号：US10824922

申请日：2004-04-15

申请人： Ching-Pang Lee ,  Ronald Scott Bunker

发明人： Ching-Pang Lee ,  Ronald Scott Bunker

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  Y02T50/676

摘要： A turbine airfoil includes opposite pressure and suction sides joined together at leading and trailing edges. An outwardly convex nose bridge bridges the pressure and suction sides behind the leading edge, and is integrally joined to a complementary thermally insulating shield spaced therefrom to define a bridge channel. The shield includes the leading edge and wraps laterally aft around the nose bridge along both the pressure and suction sides.

摘要翻译： 涡轮机翼片包括在前缘和后缘处连接在一起的相对的压力和吸力侧。 一个向外凸起的鼻梁桥接了前缘后面的压力和吸力侧，并且与其隔开的互补隔热屏蔽件整体地接合以限定桥接通道。 护罩包括前缘，沿着压力和吸力侧在鼻梁周围侧向包裹。

公开(公告)号：US5660525A

公开(公告)日：1997-08-26

申请号：US94998

申请日：1993-07-23

申请人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

发明人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2260/202

摘要： A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. The holes are also disposed in converging pairs to impinge together in the slot the first fluid channeled therethrough. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.

摘要翻译： 适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。 孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。 这些孔也以会聚对设置，以将槽中的第一流体冲入其中。 在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

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

IPC分类号： F01D5/18 ,  F01D5/14 ,  B23P15/04

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。

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

IPC分类号： F01D5/18 ,  B24C1/04 ,  C23C4/04 ,  F01D5/28

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。