公开(公告)号：US09010125B2

公开(公告)日：2015-04-21

申请号：US13956405

申请日：2013-08-01

Applicant: Jay A. Morrison ,  Ching-Pang Lee ,  Michael E. Crawford

Inventor： Jay A. Morrison ,  Ching-Pang Lee ,  Michael E. Crawford

IPC: F01D9/02

CPC classification number: F01D9/023 ,  F01D25/12 ,  F05D2260/201 ,  F23R3/002 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20150033697A1

公开(公告)日：2015-02-05

申请号：US13956405

申请日：2013-08-01

Applicant: Jay A. Morrison ,  Ching-Pang Lee ,  Michael E. Crawford

Inventor： Jay A. Morrison ,  Ching-Pang Lee ,  Michael E. Crawford

IPC: F01D9/02

CPC classification number: F01D9/023 ,  F01D25/12 ,  F05D2260/201 ,  F23R3/002 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08826668B2

公开(公告)日：2014-09-09

申请号：US13195947

申请日：2011-08-02

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: H01L23/46 ,  F23R3/06 ,  F01D9/02 ,  F01D25/12 ,  F01D5/18

CPC classification number: F01D5/186 ,  F01D9/023 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y10S165/908

Abstract: A system for cooling a wall (24) of a component having an outer surface with raised ribs (12) defining a structural pocket (10), including: an inner wall (26) within the structural pocket and separating the wall outer surface within the pocket into a first region (28) outside of the inner wall and a second region (40) enclosed by the inner wall; a plate (14) disposed atop the raised ribs and enclosing the structural pocket, the plate having a plate impingement hole (16) to direct cooling air onto an impingement cooled area (38) of the first region; a cap having a skirt (50) in contact with the inner wall, the cap having a cap impingement hole (20) configured to direct the cooling air onto an impingement cooled area (44) of the second region, and; a film cooling hole (22) formed through the wall in the second region.

Abstract translation: 一种用于冷却具有外表面的部件的壁（24）的系统，所述外壁具有限定结构袋（10）的凸肋（12），包括：在所述结构袋内的内壁（26），并将所述壁外表面分开 口袋进入内壁外部的第一区域（28）和被内壁包围的第二区域（40）; 设置在所述凸肋顶部并包围所述结构袋的板（14），所述板具有板冲击孔（16），以将冷却空气引导到所述第一区域的冲击冷却区域（38）上; 具有与所述内壁接触的裙部（50）的盖，所述盖具有盖冲击孔（20），所述盖冲击孔构造成将所述冷却空气引导到所述第二区域的冲击冷却区域（44）上; 在所述第二区域中穿过所述壁形成的薄膜冷却孔（22）。

公开(公告)号：US08667682B2

公开(公告)日：2014-03-11

申请号：US13094966

申请日：2011-04-27

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: B21D53/00

CPC classification number: B21K3/00 ,  F01D9/023 ,  F05D2260/201 ,  F23R3/425 ,  F23R3/46

Abstract: A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).

Abstract translation: 一种形成具有多面板外壁的内燃机部件的方法。 多面板外壁具有带有内表面（18）和外表面（37）的内板（16）。 内板外表面（37）具有由整体结构肋（38）形成的分立的袋（23）。 每个袋（23）在袋（23）和集气室（20）之间具有膜冷却孔（31）。 该方法包括：在中间板（22）中形成凹坑（40），至少一个具有喷嘴（29）的凹坑（40）; 将所述中间板（22）固定到所述内板外表面（37）上，从而封闭至少一个凹槽（23）; 并且确保具有喷嘴（29）的相应的凹坑（40）突出到相应的封闭的袋（24）中，并且相应的喷嘴（29）构造成将相应的冷却流体喷射（35）引导到内板的外表面 相应的封闭口袋（23）。

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：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：US08894363B2

公开(公告)日：2014-11-25

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，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：US20120121408A1

公开(公告)日：2012-05-17

申请号：US12945948

申请日：2010-11-15

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: F04D29/40

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

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：US09085981B2

公开(公告)日：2015-07-21

申请号：US13655675

申请日：2012-10-19

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: F01D9/06 ,  F23R3/02 ,  F23R3/06 ,  F23R3/54 ,  F01D9/02 ,  F23R3/00

CPC classification number: F01D9/023 ,  F05D2260/20 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R3/54 ,  F23R2900/03045

Abstract: A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).

Abstract translation: 一种用于罐式环形燃气涡轮发动机的管道装置（10），包括：设置在燃烧器（16）和第一排涡轮叶片之间并在其中限定热气体通道（30）的管道（12,14），所述管道 （12,14），其具有结合到外表面（80）中的凸起的几何特征（54）; 以及流动套筒（72），其限定在所述流动套筒（72）的内表面（78）和所述管道外表面（80）之间的冷却流动路径（84）。 在冷却流体（86）穿过相对上游的凸起的几何特征（90）之后，流动套筒（72）的内表面（78）有效地将冷却流体（86）引导到将相对 上游凸起几何特征（90）从相对下游凸起的几何特征（94）。

公开(公告)号：US08959886B2

公开(公告)日：2015-02-24

申请号：US12832124

申请日：2010-07-08

Applicant: Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison

IPC: F23R3/06 ,  F23R3/00 ,  F01D9/02

CPC classification number: F23R3/005 ,  F01D9/023 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.

Abstract translation: 热燃气通过燃气涡轮发动机的导管。 导管包括具有内表面，外表面，区域，入口和出口的壁结构。 内表面限定导管的内部容积。 该区域在内表面和外表面之间延伸并且包括限定多个冷却通道的冷却流体结构。 入口从外表面向内延伸，并在入口和通道之间提供流体连通。 出口从通道延伸到内表面以在通道和内部容积之间提供流体连通。 至少一个第一冷却通道与至少一个第二冷却通道相交，使得流过第一冷却通道的冷却流体与流过第二冷却通道的冷却流体相互作用。