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1. 发明授权

US07134842B2 Scalloped surface turbine stage 有权
标题翻译：扇形水轮机平台
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。

2. 发明授权

US08884182B2 Method of modifying the end wall contour in a turbine using laser consolidation and the turbines derived therefrom 有权
标题翻译：使用激光固结改变涡轮机端壁轮廓的方法和从其获得的涡轮机
公开(公告)号：US08884182B2
公开(公告)日：2014-11-11
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： B23K26/00 , B23P6/00 , B64C11/00 , F01D5/20 , B22F5/00 , C23C24/10 , B22F3/105 , F01D5/14 , C23C26/02 , B22F5/04
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： A method of modifying an end wall contour is provided. The method includes creating a weld pool using a laser, 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. The weld pool is created on a turbine component and contains molten metal or ceramic derived as a result of a heat interaction between the laser and the turbine component.
摘要翻译：提供了修改端壁轮廓的方法。该方法包括使用激光产生熔池，向熔池中加入金属或陶瓷粉末或线填料，并以导致约0.005至约50体积百分比变化的方式改变涡轮机部分涡轮机的一部分。焊池在涡轮机部件上产生并且包含由于激光器和涡轮机部件之间的热相互作用导致的熔融金属或陶瓷。

3. 发明授权

US08319146B2 Method and apparatus for laser cutting a trench 有权
标题翻译：用于激光切割沟槽的方法和装置
公开(公告)号：US08319146B2
公开(公告)日：2012-11-27
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。

4. 发明授权

US07328580B2 Chevron film cooled wall 有权
标题翻译：雪佛龙薄膜冷却墙
公开(公告)号：US07328580B2
公开(公告)日：2008-02-12
申请号：US10874900
申请日：2004-06-23
申请人： Ching-Pang Lee , Steven Robert Brassfield , Ronald Scott Bunker
发明人： Ching-Pang Lee , Steven Robert Brassfield , Ronald Scott Bunker
IPC分类号： F23R3/42
CPC分类号： B23K26/384
摘要： A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.
摘要翻译：燃气涡轮发动机中的壁包括内表面和外表面，其具有穿过其延伸的一排复合人字形薄膜冷却孔。人字形孔在壁内表面的入口和壁外表面的人字形出口之间纵向和横向分开。

5. 发明授权

US07186091B2 Methods and apparatus for cooling gas turbine engine components 失效
标题翻译：用于冷却燃气涡轮发动机部件的方法和装置
公开(公告)号：US07186091B2
公开(公告)日：2007-03-06
申请号：US10984292
申请日：2004-11-09
申请人： Ching-Pang Lee , Ronald Scott Bunker , Harvey Michael Maclin , Ramgopal Darolia
发明人： Ching-Pang Lee , Ronald Scott Bunker , Harvey Michael Maclin , Ramgopal Darolia
IPC分类号： F01D5/18
CPC分类号： F23R3/002 , F01D5/183 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2300/611 , F23R2900/03041
摘要： A method of cooling a gas turbine engine component having a perforate metal wall includes providing a plurality of pores in the wall, wherein the pores extend substantially perpendicularly through the wall, and wherein the pores are covered and sealed closed at first ends thereof by a thermal barrier coating disposed over a first surface of the wall, and providing a plurality of film cooling holes in the wall, wherein the holes extend substantially perpendicularly through the wall and the thermal barrier coating. The method also includes providing cooling fluid to the plurality of pores and the plurality of film cooling holes along a second surface of the wall, channeling the cooling fluid through the pores for back side cooling an inner surface of the thermal barrier coating, and channeling the cooling fluid through the holes for film cooling an outer surface of the thermal barrier coating.
摘要翻译：一种冷却具有穿孔金属壁的燃气涡轮发动机部件的方法包括在壁中提供多个孔，其中孔基本上垂直延伸穿过壁，并且其中孔在其第一端被热封屏障涂层，其设置在所述壁的第一表面上，并且在所述壁中提供多个膜冷却孔，其中所述孔基本上垂直延伸穿过所述壁和所述热障涂层。该方法还包括沿着壁的第二表面向多个孔和多个膜冷却孔提供冷却流体，将冷却流体引导通过孔，用于背面冷却热障涂层的内表面，并且引导冷却流体通过孔，用于薄膜冷却隔热涂层的外表面。

6. 发明授权

US06984102B2 Hot gas path component with mesh and turbulated cooling 失效
标题翻译：热气路组件与网状和紊流冷却
公开(公告)号：US06984102B2
公开(公告)日：2006-01-10
申请号：US10718003
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： F01D5/20 , F01D5/187 , F05D2260/2212 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
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 turbulators are 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。多个扰流器设置在壁的内部和外部的至少一个上。

7. 发明授权

US06234755B1 Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture 有权
标题翻译：用于改善气态冷却剂流的冷却效果的方法以及相关的制品
公开(公告)号：US06234755B1
公开(公告)日：2001-05-22
申请号：US09411206
申请日：1999-10-04
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Ching-Pang Lee , Nesim Abuaf
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Ching-Pang Lee , Nesim Abuaf
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F01D5/288 , F01D25/12 , F05D2230/90 , F05D2260/202 , F05D2260/221 , F05D2300/611 , Y02T50/67 , Y02T50/676
摘要： A method is described for improving the cooling effectiveness of a fluid which flows through a row of passage holes in a substrate (e.g., a turbine component), out to a high-temperature surface of the substrate. The method involves forming a slot over the holes, within the high temperature surface of the substrate. The slot can be formed within protective coatings applied over the substrate. Alternatively, it can be formed partially within the substrate, and partially within the protective coatings. Movement of a film coolant through the substrate and into the slot results in greater cooling effectiveness. Related articles are also described.
摘要翻译：描述了一种用于改善流过基板（例如，涡轮机部件）中的一排通道孔的流体到基板的高温表面的冷却效率的方法。该方法包括在衬底的高温表面内在孔上形成槽。槽可以形成在施加在基板上的保护涂层内。或者，其可以部分地形成在基底内，部分地形成在保护性涂层内。薄膜冷却剂通过基底并进入槽中的运动导致更大的冷却效果。还描述了相关文章。

8. 发明授权

US5651662A Film cooled wall 失效
标题翻译：薄膜冷却墙
公开(公告)号：US5651662A
公开(公告)日：1997-07-29
申请号：US968544
申请日：1992-10-29
申请人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf
发明人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf
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. 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。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。

9. 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。

10. 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。

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