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51. 发明授权

US06422821B1 Method and apparatus for reducing turbine blade tip temperatures 失效
标题翻译：降低涡轮叶片尖端温度的方法和装置
公开(公告)号：US06422821B1
公开(公告)日：2002-07-23
申请号：US09756902
申请日：2001-01-09
申请人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
发明人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F05D2240/121 , F05D2240/303 , F05D2250/70 , F05D2260/202
摘要： A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.
摘要翻译：描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。在翼型件前缘处的第一和第二尖端壁之间限定了切口。第二末端壁的至少一部分被凹入以限定尖端架。

52. 发明授权

US5503527A Turbine blade having tip slot 失效
标题翻译：涡轮叶片具有尖端槽
公开(公告)号：US5503527A
公开(公告)日：1996-04-02
申请号：US329750
申请日：1994-12-19
申请人： Ching-Pang Lee , Edward F. Pietraszkiewicz , Chander Prakash , Ronald D. Zerkle
发明人： Ching-Pang Lee , Edward F. Pietraszkiewicz , Chander Prakash , Ronald D. Zerkle
IPC分类号： F01D5/20 , F01D5/18
CPC分类号： F01D5/20 , Y02T50/673
摘要： A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.
摘要翻译：燃气涡轮发动机转子叶片包括具有在前缘和后缘处连接在一起的第一和第二侧壁的翼型件。第一和第二尖端壁沿着相应的第一和第二侧壁的相邻前缘延伸到邻近的后缘并且间隔开以限定其间的尖端腔。第一凹口设置在与前缘相邻的第一末端壁中，用于将一部分可在翼型上流动的燃烧气体引导到尖端腔中，以减少气体在叶片尖端上的加热效应。在优选实施例中，第二凹口设置成与后缘相邻，用于促进从第一凹口流过尖端空腔。

53. 发明授权

US5458461A Film cooled slotted wall 失效
标题翻译：薄膜冷却开槽墙
公开(公告)号：US5458461A
公开(公告)日：1995-10-17
申请号：US354194
申请日：1994-12-12
申请人： Ching-Pang Lee , Chander Prakash , John H. Starkweather , Ronald D. Zerkle
发明人： Ching-Pang Lee , Chander Prakash , John H. Starkweather , Ronald D. Zerkle
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2260/202
摘要： A wall adapted for use in a gas turbine engine between a first fluid and a second hotter 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 partly inwardly and perpendicularly from the second side toward the first side and is provided with the first fluid through a plurality of longitudinally spaced apart holes. The holes are aligned coplanar with the slot and longitudinally inclined to effect longitudinal overlapping of the first fluid inside the slot prior to discharge therefrom as a substantially continuous film.
摘要翻译：适于在第一流体和第二热流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。细长槽从第二侧向第一侧部分地向内并垂直延伸，并且通过多个纵向间隔开的孔设置有第一流体。孔与槽对齐并且纵向倾斜以在将槽排出之前的第一流体作为基本上连续的膜进行纵向重叠。

54. 发明授权

US09630277B2 Airfoil having built-up surface with embedded cooling passage 有权
公开(公告)号：US09630277B2
公开(公告)日：2017-04-25
申请号：US12723880
申请日：2010-03-15
申请人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
发明人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
IPC分类号： F02C7/12 , B23P6/00 , F01D5/00 , F01D5/14 , F01D5/18
CPC分类号： B23P6/007 , F01D5/005 , F01D5/145 , F01D5/186 , F05D2230/30 , F05D2230/80 , F05D2240/81 , Y10T29/49318
摘要： A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

55. 发明授权

US09347324B2 Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles 有权
标题翻译：具有冲击插入件的涡轮机翼型叶片具有多个冲击喷嘴
公开(公告)号：US09347324B2
公开(公告)日：2016-05-24
申请号：US14133773
申请日：2013-12-19
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , F01D9/04 , F05D2210/33 , F05D2240/12 , F05D2240/127 , F05D2260/2212
摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.
摘要翻译：涡轮叶片包括大致细长的中空翼型件和冷却系统。冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线从至少一个相邻的冲击孔流出的冷却流体。

56. 发明授权

US09133721B2 Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine 有权
标题翻译：涡轮转换部件由用于燃气涡轮发动机的两段风冷多层外板形成
公开(公告)号：US09133721B2
公开(公告)日：2015-09-15
申请号：US12945948
申请日：2010-11-15
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： F23R3/46 , F01D9/02 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

57. 发明授权

US09028207B2 Cooled component wall in a turbine engine 有权
标题翻译：在涡轮发动机中冷却的部件壁
公开(公告)号：US09028207B2
公开(公告)日：2015-05-12
申请号：US12888467
申请日：2010-09-23
申请人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
发明人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

58. 发明申请

US20150118057A1 MULTI-WALL GAS TURBINE AIRFOIL CAST USING A CERAMIC CORE FORMED WITH A FUGITIVE INSERT AND METHOD OF MANUFACTURING SAME 有权
标题翻译：多层气体涡轮机空气采用陶瓷铸造而成，具有易燃插件及其制造方法
公开(公告)号：US20150118057A1
公开(公告)日：2015-04-30
申请号：US14068061
申请日：2013-10-31
申请人： Ching-Pang Lee , Gary B. Merrill
发明人： Ching-Pang Lee , Gary B. Merrill
IPC分类号： F01D5/14 , B22C9/24 , B22C9/10
CPC分类号： B22C9/24 , B22C7/02 , B22C9/10 , B22C21/14 , F01D5/147 , F01D5/187 , F05D2230/211
摘要： A multi-wall gas turbine airfoil (192) and method of forming same using a casting core (150) having a monolithic body configured to define a pressure side wall (12), a suction side wall (14), and a third wall (16). The casting core is formed around a fugitive insert (96) during a single pour casting process.
摘要翻译：一种多壁燃气轮机翼型（192）及其使用具有整体式铸件（150）的成形方法，所述整体式主体构造成限定压力侧壁（12），吸力侧壁（14）和第三壁（ 16）。在单次浇铸过程期间，铸芯在短片（96）周围形成。

59. 发明授权

US09010125B2 Regeneratively cooled transition duct with transversely buffered impingement nozzles 有权
标题翻译：具有横向缓冲冲击喷嘴的再生冷却过渡管道
公开(公告)号：US09010125B2
公开(公告)日：2015-04-21
申请号：US13956405
申请日：2013-08-01
申请人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
发明人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R3/002 , F23R2900/03043 , F23R2900/03044
摘要： A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.
摘要翻译：一种冷却装置（56），其具有：构造成从燃烧器接收热气体（16）的管道（30）以及围绕所述管道并且在其间限定冷却气室（52）的流动套管（50），其中所述流动套筒构造成形成从所述流动套筒中的凹坑（82）发出的冲击冷却喷嘴（70），其有效地主要地冷却（60）中的管道，并且其中所述流动套管限定有效地仅通过交叉流（76）来冷却所述管道的对流冷却区域（64），所述交叉流动包括冷却流体（72）从冲击冷却区。在冲击冷却区域中，随着未折射部分靠近对流冷却区，流动套管的未折弯部分（84）从导管逐渐变细。流动套筒构造成在对流冷却区域中产生比在冲击冷却区域更大的交叉流速度。

60. 发明授权

US08985949B2 Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly 有权
标题翻译：在翼型组件的后缘部分包括波浪冷却室的冷却系统
公开(公告)号：US08985949B2
公开(公告)日：2015-03-24
申请号：US13872229
申请日：2013-04-29
申请人： Ching-Pang Lee , Ralph W. Matthews , Gm Salam Azad , Manjit Shivanand
发明人： Ching-Pang Lee , Ralph W. Matthews , Gm Salam Azad , Manjit Shivanand
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2240/304 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/294 , F05D2260/201 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.
摘要翻译：燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和冷却系统。外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。冷却系统接收来自冷却流体腔的冷却流体，用于冷却外壁的后缘部分，并且包括由相对的第一和第二侧壁限定的冷却流体室，该第一和第二侧壁包括相应的交替成角度的部分，这些部分为冷却流体室提供Z字形。

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