公开(公告)号：WO2014143413A3

公开(公告)日：2014-12-18

申请号：PCT/US2014012525

申请日：2014-01-22

Applicant: SIEMENS AG ,  LEE CHING-PANG

Inventor： LEE CHING-PANG

IPC: F01D11/00 ,  F01D5/08 ,  F01D11/04

CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2240/80 ,  F05D2250/37 ,  F05D2250/38 ,  F05D2250/71 ,  F05D2260/14

Abstract: A seal assembly (50) between a disc cavity and a turbine section (26) hot gas path includes a stationary vane assembly (12) with an inner shroud (16) and a rotating blade assembly (18) downstream from the vane assembly and including a plurality of blades that are supported on a platform (28) and rotate with a turbine rotor and the platform during operation of the engine. The inner shroud (16) comprises a radially innwardly facing suface (46) comprising vane grooves (60), and the platform includes a radially and axially facing surface (146), and a plurality of grooves (160) extending into the said surface. The grooves (60, 160) are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract translation: 在盘腔和涡轮部分（26）热气路径之间的密封组件（50）包括具有内护罩（16）和在叶片组件下游的旋转叶片组件（18）的静止叶片组件（12），并且包括 多个叶片，其被支撑在平台（28）上并在发动机运行期间与涡轮转子和平台一起旋转。 内护罩（16）包括径向向内面向的包括叶片槽（60）的表面（46），并且所述平台包括径向和轴向面对的表面（146）以及延伸到所述表面中的多个凹槽（160）。 凹槽（60,160）被布置成使得在相邻凹槽之间形成空间。 在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

公开(公告)号：WO2014085464A1

公开(公告)日：2014-06-05

申请号：PCT/US2013/072022

申请日：2013-11-26

Applicant: SIEMENS AKTIENGESELLSCHAFT ,  LEE, Ching-Pang ,  THAM, Kok-Mun ,  VITT, Paul H. ,  SCHROEDER, Eric

Inventor： LEE, Ching-Pang ,  THAM, Kok-Mun ,  VITT, Paul H. ,  SCHROEDER, Eric

IPC: F01D5/14 ,  F01D11/00 ,  F01D11/02

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D11/001 ,  F01D11/02

Abstract: A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.

Abstract translation: 一种燃气涡轮发动机，包括：多个叶片（60），其组装成环形叶片的叶片并且部分地限定热气体路径（26）和冷却流体路径（24），其中冷却流体路径从转子腔 （22）到热气路径; 设置在所述一排叶片的基部（76）的侧面（74）上的天使翼组件（99） 以及围绕天使翼组件分布的泵送特征（130），其被配置为在冷却流体路径的最窄间隙（42）处施加对流过其的冷却流体流的运动。 多个泵送特征，天使翼组件和叶片排的基部有效地在冷却流体进入热气体路径时产生螺旋运动。

公开(公告)号：WO2014039288A1

公开(公告)日：2014-03-13

申请号：PCT/US2013/056379

申请日：2013-08-23

Applicant: SIEMENS AKTIENGESELLSCHAFT ,  LEE, Ching-Pang ,  LANDRUM, Evan C. ,  ZHANG, Jiping

Inventor： LEE, Ching-Pang ,  LANDRUM, Evan C. ,  ZHANG, Jiping

IPC: F01D21/00 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18

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。 该系统在发动机的小于满载运行期间运行，以使燃烧器壳体内的空气循环，但是在发动机的全负载运行期间不起作用

公开(公告)号：WO2012112318A1

公开(公告)日：2012-08-23

申请号：PCT/US2012/023787

申请日：2012-02-03

Applicant: SIEMENS ENERGY, INC. ,  LEE, Ching-Pang ,  JIANG, Nan ,  MARRA, John J. ,  RUDOLPH, Ronald J. ,  DALTON, John P.

Inventor： LEE, Ching-Pang ,  JIANG, Nan ,  MARRA, John J. ,  RUDOLPH, Ronald J. ,  DALTON, John P.

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/2212

Abstract: A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.

Abstract translation: 连续的蛇形冷却回路，形成在涡轮机翼型件（24）的MID区域中的压力和吸力侧壁（52,54）之间的径向通道（44,45,46,47A，48A）的进展。 电路首先轴向前进，然后切向地结束于邻近吸力侧（54）并且不与压力侧（52）相邻的最后一个径向通道（48A）。 轴向行进（44,45,46）的通道可以与翼型件的压力和吸力侧壁相邻。 最后一个径向通道（47A）的下一个可以与压力侧壁相邻并且不与吸力侧壁相邻。 最后两个径向通道（47A，48A）可以沿着压力和吸力侧壁分别比在宽度方向上更长，从而在这些热壁的内部提供增加的直接冷却表面积。

公开(公告)号：WO2012021194A2

公开(公告)日：2012-02-16

申请号：PCT/US2011/037084

申请日：2011-05-19

Applicant: SIEMENS ENERGY, INC. ,  LEE, Ching-Pang ,  UM, Jae Y. ,  MUNSHI, Mrinal ,  ZUNIGA, Humberto A.

Inventor： LEE, Ching-Pang ,  UM, Jae Y. ,  MUNSHI, Mrinal ,  ZUNIGA, Humberto A.

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：WO2011153182A1

公开(公告)日：2011-12-08

申请号：PCT/US2011/038672

申请日：2011-06-01

Applicant: SIEMENS ENERGY, INC. ,  MIKRO SYSTEMS, INC. ,  LEE, Ching-Pang ,  MERRILL, Gary B. ,  BURNS, Andrew J.

Inventor： LEE, Ching-Pang ,  MERRILL, Gary B. ,  BURNS, Andrew J.

IPC: B22C7/02 ,  B22C9/04

CPC classification number: B22C9/043 ,  B22C7/02 ,  B22C7/026 ,  B22C9/04 ,  B22C9/22 ,  B22D17/00 ,  B22D29/00 ,  Y10T428/12361

Abstract: A method of casting a component (42) having convoluted interior passageways (44). A desired three dimensional structure corresponding to a later-formed metal alloy component is formed by stacking a plurality of sheets (18, 20) of a fugitive material. The sheets contain void areas (22) corresponding to a desired interior passageway in the metal alloy component. A ceramic slurry material is cast into the three dimensional structure to form either a ceramic core (34) or a complete ceramic casting vessel (38). If just a ceramic core is formed, a wax pattern is formed around the ceramic core and an exterior ceramic shell (38) is formed around the wax pattern by a dipping process prior to the removal of the fugitive material and wax. An alloy component having the desired interior passageway is cast into the casting vessel after the fugitive material is removed

Abstract translation: 一种铸造具有卷曲内部通道（44）的部件（42）的方法。 对应于后来形成的金属合金部件的期望的三维结构通过堆叠多个片状物（18,20）而形成。 这些板包含对应于金属合金部件中期望的内部通道的空隙区域（22）。 将陶瓷浆料材料铸造成三维结构以形成陶瓷芯（34）或完整的陶瓷铸造容器（38）。 如果仅形成陶瓷芯，则在陶瓷芯周围形成蜡图案，并且在除去逸散材料和蜡之前通过浸渍工艺在蜡图案周围形成外部陶瓷壳（38）。 具有所需内部通道的合金部件在除去逸散材料之后被浇注入铸造容器中

公开(公告)号：WO2011050025A2

公开(公告)日：2011-04-28

申请号：PCT/US2010053317

申请日：2010-10-20

Applicant: SIEMENS ENERGY INC ,  LEE CHING-PANG ,  MARRA JOHN J ,  MIKRO SYSTEMS INC

Inventor： LEE CHING-PANG ,  MARRA JOHN J

IPC: F01D5/18

CPC classification number: F01D5/187 ,  B22C9/103 ,  F05D2230/21 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/18 ,  F05D2250/292

Abstract: A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).

Abstract translation: 一种用于其中的燃气涡轮发动机（10）和翼型件（50），所述翼型件（50）具有包括在室（100）和一系列孔（78）之间延伸的冷却通道（110,120）的结构（128） ），其沿着所述后缘（72）定位，从所述腔室（100）接收的冷却流体（144）通过所述后缘离开所述翼型件），其中所述结构（128）的特征在于所述压力和吸力 作为沿着冷却通道（110,120）的位置的函数的翼型件的侧壁（74,76），使得在多个冷却通道中的每一个的特征在于作为功能减小的横截面流动面积（170,174） 距离室（100）的距离。

公开(公告)号：WO2010074930A1

公开(公告)日：2010-07-01

申请号：PCT/US2009/066833

申请日：2009-12-04

Applicant: GENERAL ELECTRIC COMPANY ,  PANDEY, Vidhu, Shekhar ,  LEE, Ching-Pang ,  SCHILLING, Jan, Christopher ,  WADIA, Aspi, Rustom ,  KEITH, Brian, David ,  CLEMENTS, Jeffrey, Donald

Inventor： PANDEY, Vidhu, Shekhar ,  LEE, Ching-Pang ,  SCHILLING, Jan, Christopher ,  WADIA, Aspi, Rustom ,  KEITH, Brian, David ,  CLEMENTS, Jeffrey, Donald

IPC: F01D5/14 ,  F01D5/30

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

Abstract: A turbine blade (10) includes an airfoil (16) and integral platform at the root thereof. The platform (18) is contoured in elevation from a ridge (36, 48) to a trough (38), and is curved axially to complement the next adjacent curved platform.

Abstract translation: 涡轮叶片（10）包括在其根部处的翼型件（16）和整体式平台。 平台（18）从脊（36,48）到槽（38）的高度方向轮廓，并且轴向弯曲以补充下一个相邻弯曲平台。

公开(公告)号：WO2010051110A9

公开(公告)日：2010-05-06

申请号：PCT/US2009/057374

申请日：2009-09-18

Applicant: GENERAL ELECTRIC COMPANY ,  SCOGGINS, Patrick, Jarvis ,  LAFLEN, James, Harvey ,  LEE, Ching-Pang ,  FROST, Wilson

Inventor： SCOGGINS, Patrick, Jarvis ,  LAFLEN, James, Harvey ,  LEE, Ching-Pang ,  FROST, Wilson

IPC: F01D9/04 ,  F01D25/24

Abstract: A turbine nozzle (24) includes a row of vanes (38) extending radially between annular outer and inner bands (34,36). The outer band (34) includes a pair of radial flanges (46-52) defining an annular seal groove (54,56) therebetween. One of the flanges (46-52) is crenelated to improve nozzle life.

公开(公告)号：WO2014066495A1

公开(公告)日：2014-05-01

申请号：PCT/US2013/066369

申请日：2013-10-23

Applicant: SIEMENS AKTIENGESELLSCHAFT ,  MIKRO SYSTEMS, INC. ,  LEE, Ching-Pang ,  HENEVELD, Benjamin E.

Inventor： LEE, Ching-Pang ,  HENEVELD, Benjamin E.

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2250/185 ,  F05D2260/22141

Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.

Abstract translation: 一种用于燃气涡轮发动机部件的冷却装置（82），所述冷却装置（82）具有多排（92,94,96）的翼型件（98），其中在一排（92,94）内相邻的翼型件 ，96）限定冷却通道（90）的段（110,130,140），并且其中一排（92,94）中的段（110,130）的出口（114,134）在空气动力学上与入口（132， 142）在相邻排（94,96）中的段（130,140），以限定具有非连续壁（116,120）的连续冷却通道（90），每个冷却通道（90）包括蛇形形状。