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1. 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。

2. 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。

3. 发明授权

US07186084B2 Hot gas path component with mesh and dimpled cooling 失效
标题翻译：热气路组件带有网状和凹凸冷却
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。

4. 发明授权

US07493767B2 Method and apparatus for cooling combustor liner and transition piece of a gas turbine 有权
标题翻译：一种用于冷却燃气轮机的燃烧器衬套和过渡件的方法和装置
公开(公告)号：US07493767B2
公开(公告)日：2009-02-24
申请号：US10907866
申请日：2005-04-19
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
摘要翻译：一种用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个湍流器的燃烧器衬套，该多个湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将冷却空气从所述压缩机排出口引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。

5. 发明授权

US07373778B2 Combustor cooling with angled segmented surfaces 有权
标题翻译：燃烧器冷却具有成角度的分段表面
公开(公告)号：US07373778B2
公开(公告)日：2008-05-20
申请号：US10711131
申请日：2004-08-26
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson
IPC分类号： F02C1/00
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F02C7/18 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F23R3/005
摘要： A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about the outside surface. A space is disposed between each of said plurality of angled strips so as to create vortices in a cooling air flowing in a longitudinal direction across said outside surface of said combustor liner. A method of fabricating a combustor liner includes forming a plurality of angled strips on an outside surface of the combustor liner and arranged in an array about the outside surface, each of the angled strips is disposed so as to be spaced apart to create vortices in a cooling air flowing across the outside surface of the combustor liner.
摘要翻译：用于燃气轮机的燃烧器衬套包括在燃烧器衬套的外表面上具有多个成角度的条带的主体。多个成角度的条带围绕外表面布置成阵列。在所述多个成角度的条带中的每一个之间设置一个空间，以便在穿过所述燃烧器衬套的所述外表面沿纵向方向流动的冷却空气中产生涡流。一种制造燃烧器衬套的方法包括在燃烧器衬套的外表面上形成多个成角度的带，并围绕外表面排列成阵列，每个成角度的带被设置为间隔开以形成涡流流过燃烧器衬套的外表面的冷却空气。

6. 发明授权

US06350102B1 Shroud leakage flow discouragers 有权
标题翻译：护罩泄漏流disc disc
公开(公告)号：US06350102B1
公开(公告)日：2002-02-26
申请号：US09575704
申请日：2000-07-19
申请人： Jeremy Clyde Bailey , Ronald Scott Bunker
发明人： Jeremy Clyde Bailey , Ronald Scott Bunker
IPC分类号： F01D520
CPC分类号： F01D11/02 , F01D5/20 , F01D11/08
摘要： A turbine assembly includes a plurality of rotor blades comprising a root portion, an airfoil having a pressure sidewall and a suction sidewall, and a top portion having a cap. An outer shroud is concentrically disposed about said rotor blades, said shroud in combination with said tip portions defining a clearance gap. At least one circumferential shroud leakage discourager is disposed within the shroud. The leakage discourager(s) increase the flow resistance and thus reduce the flow of hot gas flow leakage for a given pressure differential across the clearance gap to improve overall turbine efficiency.
摘要翻译：涡轮组件包括多个转子叶片，其包括根部部分，具有压力侧壁的翼型件和抽吸侧壁以及具有盖的顶部部分。围绕所述转子叶片同心地设置外护罩，所述护罩与所述末端部分组合形成间隙。至少一个周向护罩泄漏disc is器设置在护罩内。泄漏劝阻者增加流动阻力，从而减少跨越间隙的给定压差的热气流泄漏流，以提高总体涡轮机效率。

7. 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。

8. 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。

9. 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。

10. 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。

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