公开(公告)号：US06743350B2

公开(公告)日：2004-06-01

申请号：US10063087

申请日：2002-03-18

申请人： Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang ,  Lawrence Bernard Kool

发明人： Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang ,  Lawrence Bernard Kool

IPC分类号： B23H1100

CPC分类号： B23H9/16 ,  B23H9/10

摘要： An electrode for rejuvenating a cooling passage within an airfoil, the electrode including a tip, an end, a conductive core extending between the tip and the end, and an insulating coating disposed on the conductive core. The insulating coating exposes a number of conductive strips of the conductive core extending between the tip and the end. The insulating coating forms a number of insulating portions and further exposes a number of spacer portions of the conductive core longitudinally positioned between the insulating portions. The insulating portions substantially span a distance between the tip and the end and are positioned between the conductive strips.

摘要翻译： 一种用于振动翼型内的冷却通道的电极，所述电极包括尖端，端部，在尖端和端部之间延伸的导电芯，以及设置在导电芯上的绝缘涂层。 绝缘涂层暴露出在尖端和端部之间延伸的多个导电芯的导电条。 绝缘涂层形成多个绝缘部分，并进一步暴露导体芯的多个间隔部分纵向定位在绝缘部分之间。 绝缘部分基本上跨越尖端和端部之间的距离并且位于导电条之间。

公开(公告)号：US06554571B1

公开(公告)日：2003-04-29

申请号：US09683189

申请日：2001-11-29

申请人： Ching-Pang Lee ,  Bin Wei ,  Robert Alan Johnson ,  Hsin-Pang Wang

发明人： Ching-Pang Lee ,  Bin Wei ,  Robert Alan Johnson ,  Hsin-Pang Wang

IPC分类号： F04D2938

CPC分类号： F01D5/187 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141

摘要： A curved turbulator configuration is in a radial cooling passage of an airfoil, where the radial cooling passage is defined by at least a leading wall and a trailing wall, and the airfoil includes a tip and a root. The curved turbulator configuration includes a number of spaced curved turbulator pairs positioned along a center-line on an inner surface of the leading wall and a number of spaced complementary curved turbulator pairs positioned along a center-line on an inner surface of the trailing wall. An electrode for forming the curved turbulator configuration in the radial cooling passage includes a leading face having a curved turbulator pattern, a trailing face having a complementary curved turbulator pattern, a conductive core, and an insulating coating disposed thereon that is partly removed.

摘要翻译： 弯曲的湍流器构造在翼型件的径向冷却通道中，其中径向冷却通道由至少前导壁和后壁限定，并且翼型件包括尖端和根部。 弯曲的湍流器构造包括沿着前壁的内表面上的中心线定位的多个间隔开的弯曲的湍流器对，以及沿着后壁的内表面上的中心线定位的多个间隔开的互补弯曲湍流器对。 用于在径向冷却通道中形成弯曲的湍流器构造的电极包括具有弯曲的湍流器图案的前表面，具有互补弯曲湍流器图案的后表面，导电芯和位于其上的部分去除的绝缘涂层。

公开(公告)号：US06379528B1

公开(公告)日：2002-04-30

申请号：US09734035

申请日：2000-12-12

申请人： Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang

发明人： Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang

IPC分类号： B23H300

CPC分类号： B23H9/10 ,  B23H9/008 ,  F01D25/12 ,  F05D2260/2212 ,  F05D2260/22141

摘要： The back side recessed cooling surface of a shroud defining in part the hot gas path of a turbine is electrochemically machined to provide surface roughness elements and spaces therebetween to increase the heat transfer coefficient. To accomplish this, an electrode with insulating dielectric portions and non-insulating portions is disposed in opposition to the cooling surface. By passing an electrolyte between the cooling surface and electrode and applying an electrical current between the electrode and a shroud, roughness elements and spaces therebetween are formed in the cooling surface in opposition to the insulating and non-insulating portions of the electrode, hence increasing the surface area and heat transfer coefficient of the shroud.

摘要翻译： 部分限定涡轮机的热气路径的护罩的后侧凹入的冷却表面被电化学加工，以提供表面粗糙度元件和间隔，以增加传热系数。 为了实现这一点，具有绝缘电介质部分和非绝缘部分的电极设置成与冷却表面相对。 通过在冷却表面和电极之间通过电解质并在电极和护罩之间施加电流，与电极的绝缘和非绝缘部分相对地在冷却表面上形成粗糙元件和间隔，因此增加 护罩的表面积和传热系数。

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.

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。

公开(公告)号：US09206904B2

公开(公告)日：2015-12-08

申请号：US12832141

申请日：2010-07-08

申请人： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

发明人： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

IPC分类号： F16J15/32 ,  F01D11/02

CPC分类号： F16J15/3292 ,  F01D11/02 ,  F05D2240/57

摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.

摘要翻译： 一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。 密封构件包括多个柔性密封条。 每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的 轴。 密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

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。

公开(公告)号：US09121298B2

公开(公告)日：2015-09-01

申请号：US13534060

申请日：2012-06-27

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

IPC分类号： F04D11/00 ,  F01D11/00

CPC分类号： F01D11/001

摘要： A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

摘要翻译： 设置在涡轮发动机中的热气体路径和盘腔之间的密封组件包括从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片 从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。 翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。 在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中 密封组装。

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。

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。