公开(公告)号：US20130045111A1

公开(公告)日：2013-02-21

申请号：US13212282

申请日：2011-08-18

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/087 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/2212

Abstract: A cooling system for a turbine blade of a turbine engine having a bifurcated mid-chord cooling chamber for reducing the temperature of the blade. The bifurcated mid-chord cooling chamber may be formed from a pressure side serpentine cooling channel and a suction side serpentine cooling channel with cooling fluids passing through the pressure side serpentine cooling channel in a direction from the trailing edge toward the leading edge and in an opposite direction through the suction side serpentine cooling channel. The pressure side and suction side serpentine cooling channels may flow counter to each other, thereby yielding a more uniform temperature distribution than conventional serpentine cooling channels.

Abstract translation: 一种用于涡轮发动机的涡轮叶片的冷却系统，其具有用于降低叶片温度的分叉中和冷却室。 分叉中弦冷却室可以由压力侧蛇形冷却通道和吸入侧蛇形冷却通道形成，其中冷却流体沿着从后缘朝向前缘的方向通过压力侧蛇形冷却通道，并且在相反的 方向通过吸力侧蛇形冷却通道。 压力侧和吸力侧蛇形冷却通道可以相互流动，从而产生比常规蛇形冷却通道更均匀的温度分布。

公开(公告)号：US20120201674A1

公开(公告)日：2012-08-09

申请号：US13023716

申请日：2011-02-09

Applicant: Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison ,  Brede J. Kolsrud ,  John J. Marra

Inventor： Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison ,  Brede J. Kolsrud ,  John J. Marra

IPC: F01D5/18

CPC classification number: F01D5/184 ,  F01D5/186 ,  F01D5/187 ,  F05D2220/32 ,  F05D2230/51 ,  F05D2240/30 ,  F05D2240/40

Abstract: A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.

Abstract translation: 燃气轮机系统（120）中的冷却装置。 该装置包括多个流动网络单元（208），用于将热量传递到冷却流体;至少一个单元，其包括在第一壁中的开口（64a）之间的第一（218），第二（220）和第三（222） （66）和第二壁（68）中的开口以使冷却流体通过壁。 第一部分包括在第一壁的开口和第二部分之间延伸到第二部分的第一流动路径。 第三部分包括在第二部分和第二壁中的开口之间的第三流动路径，以实现冷却流体的流动。 第二部分包括在第一部分和第三部分之间的一个或多个冷却流体流动路径。 第二部分中的流动路径的数量少于第一流动路径的数量，并且少于第三流动路径的数量。

公开(公告)号：US08205458B2

公开(公告)日：2012-06-26

申请号：US11967479

申请日：2007-12-31

Applicant: Ching-Pang Lee ,  Robert Joseph Orlando

Inventor： Ching-Pang Lee ,  Robert Joseph Orlando

IPC: F01D5/18

CPC classification number: F01D25/12 ,  F01D9/041 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A duplex turbine nozzle includes a row of different first and second vanes alternating circumferentially between radially outer and inner bands in vane doublets having axial splitlines therebetween. The vanes have opposite pressure and suction sides spaced apart in each doublet to define an inboard flow passage therebetween, and corresponding outboard flow passages between doublets. The vanes have different patterns of film cooling holes with larger cooling flow density along the outboard passages than along the inboard passages.

Abstract translation: 双相涡轮喷嘴包括一排不同的第一和第二叶片，其在叶片双重体的径向外部和内部带之间周向交替，其间具有轴向分裂线。 叶片具有相反的压力和吸力侧面，每个双层间隔开，以在其间限定内侧流动通道，并且在双层之间具有相应的外侧流动通道。 叶片具有不同于薄膜冷却孔的图案，沿着外侧通道具有比沿内侧通道更大的冷却流动密度。

公开(公告)号：US20120121381A1

公开(公告)日：2012-05-17

申请号：US12945943

申请日：2010-11-15

Applicant: Richard C. Charron ,  Daniel J. Pierce ,  Jay A. Morrison ,  Ching-Pang Lee ,  Kenneth K. Landis ,  Walter Marussich

Inventor： Richard C. Charron ,  Daniel J. Pierce ,  Jay A. Morrison ,  Ching-Pang Lee ,  Kenneth K. Landis ,  Walter Marussich

IPC: F03B11/00

CPC classification number: F01D9/023 ,  F01D25/12 ,  F05D2260/201 ,  F23R2900/03044

Abstract: 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.

Abstract translation: 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：US20120076644A1

公开(公告)日：2012-03-29

申请号：US12888467

申请日：2010-09-23

Applicant: Humberto A. Zuniga ,  Ching-Pang Lee ,  Michael E. Crawford

Inventor： Humberto A. Zuniga ,  Ching-Pang Lee ,  Michael E. Crawford

IPC: F03B11/00 ,  B21D53/02

CPC classification number: F01D5/186 ,  F05D2230/90 ,  F05D2250/13 ,  F05D2250/324 ,  Y10T29/4935

Abstract: 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.

Abstract translation: 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：US20120070306A1

公开(公告)日：2012-03-22

申请号：US12884486

申请日：2010-09-17

Applicant: Ching-Pang Lee ,  John J. Marra

Inventor： Ching-Pang Lee ,  John J. Marra

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2250/70 ,  F05D2260/202 ,  F05D2260/2212

Abstract: A mesh (35) of cooling channels (35A, 35B) with an array of cooling channel intersections (42) in a wall (21, 22) of a turbine component. A mixing chamber (42A-C) at each intersection is wider (W1, W2)) than a width (W) of each of the cooling channels connected to the mixing chamber. The mixing chamber promotes swirl, and slows the coolant for more efficient and uniform cooling. A series of cooling meshes (M1, M2) may be separated by mixing manifolds (44), which may have film cooling holes (46) and/or coolant refresher holes (48).

Abstract translation: 具有在涡轮机部件的壁（21,22）中的冷却通道交叉点阵列（42）的冷却通道（35A，35B）的网状物（35）。 在每个交叉点处的混合室（42A-C）比连接到混合室的每个冷却通道的宽度（W）宽（W1，W2））。 混合室促进漩涡，并减慢冷却液的效率和均匀的冷却。 可以通过混合可以具有膜冷却孔（46）和/或冷却剂清新孔（48）的歧管（44）来分离一系列冷却网（M1，M2）。

公开(公告)号：US20120007318A1

公开(公告)日：2012-01-12

申请号：US12832141

申请日：2010-07-08

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

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

IPC: F02F11/00 ,  F16J15/44

CPC classification number: F16J15/3292 ,  F01D11/02 ,  F05D2240/57

Abstract: 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.

Abstract translation: 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：US20110305583A1

公开(公告)日：2011-12-15

申请号：US12813624

申请日：2010-06-11

Applicant: Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

Inventor： Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

IPC: F01D5/18 ,  B23P15/04

CPC classification number: F01D25/12 ,  F01D5/18 ,  F01D5/186 ,  Y10T29/4932

Abstract: A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.

Abstract translation: 形成在涡轮发动机的部件壁上的薄膜冷却结构以及制造薄膜冷却结构的方法。 膜冷却结构包括形成在壁中的多个单独的扩散部分，每个扩散部分包括单个冷却通道，用于将冷却空气朝向限定扩散部分的壁的突起引导。 膜冷却结构可以由掩模模板形成，该掩模模板包括限定壁中多个待形成的扩散部分的形状的孔。 掩模材料可以施加到壁中的掩模模板中的孔中，以便阻挡通过孔露出的冷却通道的出口。 可以去除掩模模板并且可以在壁的外表面上施加材料，使得一旦去除了掩模材料，材料就限定了扩散部分。

公开(公告)号：US20110223005A1

公开(公告)日：2011-09-15

申请号：US12723880

申请日：2010-03-15

Applicant: Ching-Pang Lee ,  Mrinal Munshi ,  Gm S. Azad ,  Jae Y. Um

Inventor： Ching-Pang Lee ,  Mrinal Munshi ,  Gm S. Azad ,  Jae Y. Um

IPC: F02C7/12 ,  B23P6/00

CPC classification number: B23P6/007 ,  F01D5/005 ,  F01D5/145 ,  F01D5/186 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2240/81 ,  Y10T29/49318

Abstract: 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.

Abstract translation: 燃气涡轮发动机中的部件包括从与翼型件相关联的平台径向向外延伸的翼型件。 翼型件包括相对的压力和吸力侧壁，其汇聚在限定在翼型的前缘处的第一位置处，以及限定在与前缘相对的翼型件的后缘处的第二位置。 该部件包括邻近压力侧壁和平台之间的交叉处的前缘的组合表面，以及至少部分地在压力侧壁和平台之间的交叉处的积层表面内的至少一个冷却通道。 至少一个冷却通道与机翼内的主冷却通道流体连通，并且在平台处具有出口，用于将冷却流体从主冷却通道直接提供到平台。

公开(公告)号：US07938951B2

公开(公告)日：2011-05-10

申请号：US11726410

申请日：2007-03-22

Applicant: Ching-Pang Lee ,  Bin Wei ,  Chen-Yu Jack Chou

Inventor： Ching-Pang Lee ,  Bin Wei ,  Chen-Yu Jack Chou

IPC: B23H9/14 ,  B23H3/04

CPC classification number: B23H9/00 ,  B23H3/00 ,  B23H3/04 ,  B23H3/06 ,  B23H9/10 ,  B23H9/14

Abstract: A method for forming holes in an object is provided. The method includes providing an electrochemical machining (ECM) electrode including a first section having insulation that circumscribes the first section, and a second section having insulation that extends only partially around the second section. The method also includes inserting the electrode into the object, such that in a single pass the electrode forms a hole that includes a first portion having a first cross-sectional area and a second portion having a second cross-sectional area.

Abstract translation: 提供了一种在物体中形成孔的方法。 该方法包括提供电化学加工（ECM）电极，其包括具有围绕第一部分的绝缘体的第一部分和具有仅部分地围绕第二部分延伸的绝缘体的第二部分。 该方法还包括将电极插入到物体中，使得在单次通过中，电极形成包括具有第一横截面积的第一部分和具有第二横截面积的第二部分的孔。