公开(公告)号：US08939717B1

公开(公告)日：2015-01-27

申请号：US14063153

申请日：2013-10-25

Applicant: Ching-Pang Lee ,  Mrinal Munshi ,  Adam C. Pela ,  Paul Bradley Davis ,  Matthew H. Lang

Inventor： Ching-Pang Lee ,  Mrinal Munshi ,  Adam C. Pela ,  Paul Bradley Davis ,  Matthew H. Lang

IPC: F01D9/04 ,  F01D25/24 ,  B23P6/00

CPC classification number: F01D25/246 ,  B23P6/005 ,  F01D9/042 ,  F05D2230/80 ,  F05D2250/61

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.

Abstract translation: 在燃气涡轮发动机的发动机部分中的一排叶片的支撑环包括环形主体部分，一排叶片固定到该环形主体部分，用于为发动机部分中的叶片提供结构支撑，以及从一个 相对于通过发动机部分的空气流动的方向，主体部分的后侧。 后钩联接到外发动机壳体，用于在发动机部分中结构地支撑支撑环。 支撑环不包括前挂钩，其具有相对于通过发动机部分的空气流的方向具有从前钩的前侧或后侧轴向延伸的凸缘。

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：US08894359B2

公开(公告)日：2014-11-25

申请号：US13314311

申请日：2011-12-08

Applicant: Mrinal Munshi ,  John Finneran ,  Ching-Pang Lee ,  Yevgeniy Shteyman ,  Daryl Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

Inventor： Mrinal Munshi ,  John Finneran ,  Ching-Pang Lee ,  Yevgeniy Shteyman ,  Daryl Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

IPC: F01D25/12 ,  F01D25/14

CPC classification number: F01D25/08

Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.

Abstract translation: 一种用于控制燃气涡轮发动机的外壳的温度的隔热/冷却系统。 所述隔热/冷却系统包括支撑在内壳体表面上的内部绝缘层，所述内部绝缘层沿着所述内壳表面周向延伸，并且提供对从外壳径向向内定位的结构的辐射能的热阻。 隔热/冷却系统还包括由面板结构限定的对流冷却通道，所述面板结构位于与外壳的外壳表面径向间隔开的关系中并围绕外壳表面的圆周延伸。 对流冷却通道形成用于冷却外壳表面的环境空气流的流路。

公开(公告)号：US08864452B2

公开(公告)日：2014-10-21

申请号：US13212273

申请日：2011-08-18

Applicant: Kok-Mun Tham ,  Ching-Pang Lee

Inventor： Kok-Mun Tham ,  Ching-Pang Lee

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F01D5/143 ,  F05D2240/80

Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.

Abstract translation: 在燃气涡轮发动机中，导流构件包括支撑在转子上的平台，径向面向的端壁，从与端壁的接合处径向向内延伸的至少一个轴向表面，从端壁径向向外延伸的翼型件和流体 流导向功能。 流体流动导向特征包括沿轴向延伸并且具有径向内部和外部凹槽端部的凹槽。 外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成用于将冷却流体引导到端壁的开口。 所述凹槽还包括从所述内槽端延伸到所述外槽端部的第一槽壁和与所述第一槽壁相对并从所述内槽端部延伸到所述外槽端部的第二槽壁。

公开(公告)号：US08764394B2

公开(公告)日：2014-07-01

申请号：US12985553

申请日：2011-01-06

Applicant: Ching-Pang Lee ,  John J. Marra ,  Gary B. Merrill ,  Benjamin E. Heneveld ,  Jill Klinger

Inventor： Ching-Pang Lee ,  John J. Marra ,  Gary B. Merrill ,  Benjamin E. Heneveld ,  Jill Klinger

IPC: F01D5/18 ,  F28F3/04 ,  F28F7/02

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2260/2214 ,  F28F3/048 ,  F28F7/02

Abstract: A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.

Abstract translation: 冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。 通道具有宽度（W1）的近壁内表面（48,50）。 内侧表面（52,54）可以会聚到减小的通道宽度（W2）。 近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。 翅片在近壁内表面的中间宽度处可能最高。 双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。 锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。

公开(公告)号：US08721291B2

公开(公告)日：2014-05-13

申请号：US13180578

申请日：2011-07-12

Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

IPC: F01D5/14

CPC classification number: F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

Abstract translation: 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

公开(公告)号：US08684684B2

公开(公告)日：2014-04-01

申请号：US12872770

申请日：2010-08-31

Applicant: Jeffrey Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

Inventor： Jeffrey Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

IPC: F01D1/02

CPC classification number: F01D9/041 ,  F01D5/143

Abstract: A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.

Abstract translation: 涡轮装置包括：第一喷嘴，包括第一叶片阵列，每个叶片包括凹压侧，凸吸入侧，以及前缘和后缘; 第一喷嘴下游的转子包括由可旋转盘承载的多个叶片; 以及设置在所述转子的下游的第二喷嘴，包括第二叶片的阵列，每个叶片包括凹压侧，凸吸入侧以及前缘和后缘; 其中所述第一和第二喷嘴的所述第一和第二叶片相对于彼此沿圆周方向定时，使得在预定操作条件下，从所述第一叶片排出的骤冷器沿周向与所述第二叶片的前缘对齐，其中 第一叶片的堆叠轴线是非线性的。 第一喷嘴的内带是非轴对称的形状。

公开(公告)号：US08668453B2

公开(公告)日：2014-03-11

申请号：US13027323

申请日：2011-02-15

Applicant: Ching-Pang Lee ,  Nan Jiang ,  John J. Marra

Inventor： Ching-Pang Lee ,  Nan Jiang ,  John J. Marra

IPC: F01D5/08

CPC classification number: F01D5/187 ,  F05D2210/33 ,  F05D2240/127 ,  F05D2250/32 ,  F05D2250/70 ,  F05D2260/2212

Abstract: A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.

Abstract translation: 公开了一种具有用于燃气涡轮发动机的具有减小质量的一个或多个销翅片的冷却系统。 冷却系统可以包括限定冷却系统的至少一部分的一个或多个第一表面。 销翅片可以从限定冷却系统的表面延伸并且可以具有大致平行于表面的非圆形截面，并且横截面的外表面的至少一部分形成至少四分之一圆。 销翅片的下游侧可以具有空腔以减小质量，从而形成更有效的涡轮机翼型件。

公开(公告)号：US20140060082A1

公开(公告)日：2014-03-06

申请号：US13603699

申请日：2012-09-05

Applicant: Ching-Pang Lee ,  Evan C. Landrum ,  Jiping Zhang

Inventor： Ching-Pang Lee ,  Evan C. Landrum ,  Jiping Zhang

IPC: F02C3/04

CPC classification number: F02C3/04 ,  F01D21/00 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18

Abstract: A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.

Abstract translation: 用于燃气涡轮发动机的壳体空气再循环系统包括位于发动机壳体壁的底壁部分和位于发动机壳体壁的顶壁部分的一个或多个入口的一个或多个出口。 该系统还包括一个在出口和入口之间提供流体连通的管道系统，用于从燃烧器壳体通过出口提取空气并将提取的空气输送到 进气口和用于选择性地允许和防止空气通过管道系统的阀系统。 该系统在发动机小于满载运行期间运行，以使燃烧器壳体内的空气循环，但是在发动机满载运行期间不起作用。

公开(公告)号：US08459956B2

公开(公告)日：2013-06-11

申请号：US12344058

申请日：2008-12-24

Applicant: Vidhu Shekhar Pandey ,  Ching-Pang Lee ,  Jan Christopher Schilling ,  Aspi Rustom Wadia ,  Brian David Keith ,  Jeffrey Donald Clements

Inventor： Vidhu Shekhar Pandey ,  Ching-Pang Lee ,  Jan Christopher Schilling ,  Aspi Rustom Wadia ,  Brian David Keith ,  Jeffrey Donald Clements

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D5/3007 ,  F05D2240/80 ,  F05D2270/17 ,  Y02T50/673

Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.

Abstract translation: 涡轮机叶片包括在其根部处的翼型件和整体式平台。 该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。