公开(公告)号：US08926267B2

公开(公告)日：2015-01-06

申请号：US13766909

申请日：2013-02-14

Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra

Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra

IPC: F01D25/12 ,  F01D5/14 ,  F01D9/06 ,  F02C7/12 ,  F01D5/18 ,  F01D5/08 ,  F01D11/00

CPC classification number: F01D5/187 ,  F01D5/082 ,  F01D5/143 ,  F01D9/065 ,  F01D11/001 ,  F01D25/12 ,  F02C7/12 ,  F05D2240/127

Abstract: A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.

Abstract translation: 一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。 周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。 通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。 预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。 预旋转器的端壁（50,54）可以是轮廓。

公开(公告)号：US08920123B2

公开(公告)日：2014-12-30

申请号：US13714518

申请日：2012-12-14

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2240/307 ,  F05D2250/185 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214

Abstract: An air cooled turbine blade including leading and trailing edges, and pressure and suction side walls extending between the leading and trailing edges. Leading and trailing edge cooling circuits extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end receiving cooling air from a final channel of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge.

Abstract translation: 包括前缘和后缘的空气冷却涡轮叶片，以及在前缘和后缘之间延伸的压力和吸力侧壁。 前缘和后缘冷却回路分别沿着前缘和后缘分别延伸。 向前流动的中段蛇形冷却回路沿横向延伸并且位于前缘和后缘冷却回路之间。 轴向尖端冷却回路在弦向延伸，位于蛇形冷却回路的外端处，位于叶片的顶盖和蛇形冷却回路之间。 轴向尖端冷却回路具有从蛇形冷却回路的最终通道接收冷却空气的前端，并排出与后缘相邻的冷却空气。

公开(公告)号：US08893510B2

公开(公告)日：2014-11-25

申请号：US13670615

申请日：2012-11-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

IPC: F02C6/04 ,  F02C7/12 ,  F01D5/08 ,  F02C7/18 ,  F01D21/00 ,  F01D25/12

CPC classification number: F02C7/18 ,  F01D5/088 ,  F01D21/00 ,  F01D25/12 ,  F05D2270/3032

Abstract: An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.

Abstract translation: 一种用于燃气涡轮发动机的空气喷射系统包括至少一个出口，通过该出口，空气仅在少于满载运行期间从发动机中抽出，至少一个转子冷却管，用于将从 出口到转子室，在一个出口和转子冷却管之间提供流体连通的管道系统，用于通过出口从发动机中提取空气的鼓风机系统， 并且将提取的空气通过管道系统和转子冷却管输送到转子室中，以及阀系统。 在全负荷发动机运行期间，阀门系统关闭，以防止空气通过管道系统，并在小于满载发动机运行期间打开以允许空气通过管道系统。

公开(公告)号：US20140338866A1

公开(公告)日：2014-11-20

申请号：US13893392

申请日：2013-05-14

Applicant: CHING-PANG LEE

Inventor： CHING-PANG LEE

IPC: F28F13/12

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2260/22141

Abstract: A cooling passage defined between first and second spaced apart sidewalls of a turbine engine component includes a turbulator system including a plurality of rows of turbulator members. Each row includes a first side turbulator member extending from the first sidewall, and a second side turbulator member extending from the second sidewall. The first and second side turbulator members are arranged such that a space is defined therebetween. The first and second side turbulator members are staggered with respect to one another such that respective forward and aft ends thereof are offset from one another. Each row further includes at least one elongate intermediate turbulator member located at least partially in the space between the respective first and second side turbulator members.

Abstract translation: 限定在涡轮发动机部件的第一和第二间隔开的侧壁之间的冷却通道包括包括多排湍流器构件的湍流器系统。 每排包括从第一侧壁延伸的第一侧湍流器构件和从第二侧壁延伸的第二侧湍流构件。 第一和第二侧面紊流器构件被布置成使得在它们之间限定空间。 第一和第二侧面紊流器构件相对于彼此交错，使得其相应的前端和后端彼此偏移。 每列还包括至少一个至少部分地位于相应的第一和第二侧面湍流器构件之间的空间中的细长的中间湍流器构件。

公开(公告)号：US08864438B1

公开(公告)日：2014-10-21

申请号：US14097319

申请日：2013-12-05

Applicant: Ching-Pang Lee ,  Gilles Carrier

Inventor： Ching-Pang Lee ,  Gilles Carrier

IPC: F01D9/02 ,  F01D5/08 ,  B23P15/04 ,  F01D5/18

CPC classification number: F01D5/188 ,  F01D9/065 ,  F05D2250/25 ,  F05D2260/2212

Abstract: A flow control insert for a turbine vane is disclosed. The flow control insert is designed to be placed in a trailing edge cooling passage of the turbine vane to simultaneously reduce cooling air flow and increase heat transfer from the vane to the cooling air, thereby improving efficiency of the turbine via reduced cooling air flow requirement while maintaining vane temperature within a specified range. Two different flow control insert designs are disclosed, where either design fits inside the cooling passage opening and allows an existing vane casting design to be used.

Abstract translation: 公开了一种用于涡轮叶片的流量控制插入件。 流量控制插入件设计成放置在涡轮叶片的后缘冷却通道中，以同时降低冷却空气流量并增加从叶片到冷却空气的传热，从而通过降低冷却空气流量要求来提高涡轮机的效率，同时 将叶片温度保持在规定的范围内。 公开了两种不同的流量控制插入物设计，其中任一种设计都适合于冷却通道开口内部并且允许使用现有的叶片铸造设计。

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：US20140227103A1

公开(公告)日：2014-08-14

申请号：US13767019

申请日：2013-02-14

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F01D5/20

Abstract: A squealer tip formed from a pressure side tip wall and a suction side tip wall extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side tip walls may be positioned along the pressure sidewall and the suction sidewall of the turbine blade, respectively. The pressure side tip wall may include a chamfered leading edge with film cooling holes having exhaust outlets positioned therein. An axially extending tip wall may be formed from at least two outer linear surfaces joined together at an intersection forming a concave axially extending tip wall. The axially extending tip wall may include a convex inner surface forming a radially outer end to an inner cavity forming a cooling system. The cooling system may include one or more film cooling holes in the axially extending tip wall proximate to the suction sidewall, which promotes increased cooling at the pressure and suction sidewalls.

Abstract translation: 公开了一种从涡轮叶片的尖端径向向外延伸的压力侧末端壁和吸力侧顶壁形成的尖叫尖端。 压力和吸力侧尖端壁可以分别沿涡轮叶片的压力侧壁和吸力侧壁定位。 压力侧末端壁可以包括倒角前缘，其中膜冷却孔具有位于其中的排气口。 轴向延伸的尖端壁可以由形成凹入的轴向延伸顶端壁的相交处的至少两个外部线性表面形成。 轴向延伸的顶端壁可以包括形成冷却系统的内腔的径向外端的凸形内表面。 冷却系统可以包括在靠近抽吸侧壁的轴向延伸的顶端壁中的一个或多个膜冷却孔，这促进了压力和吸力侧壁处的增加的冷却。

公开(公告)号：US08727716B2

公开(公告)日：2014-05-20

申请号：US12872485

申请日：2010-08-31

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

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

IPC: F01D9/04

CPC classification number: F01D9/02 ,  F01D9/04

Abstract: A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.

Abstract translation: 涡轮喷嘴包括在内带和外带之间的涡轮叶片阵列。 每个叶片包括在相对的前缘和后缘之间延伸的相对的压力和吸力侧。 叶片限定多个流动通道，每个流动通道限定在内带，外带和相邻的第一和第二叶片之间。 每个通道中的内带表面的轮廓是非轴对称的形状，包括邻近第一叶片邻近其前缘的压力侧相对较高的径向高度的峰，并且设置相对较低径向高度的槽 平行于其前缘的第二叶片后部的吸入侧并与其间隔开。 峰和槽限定协同地限定沿着第一和第二叶片之间的内带轴向延伸的弓形通道。

公开(公告)号：US08714926B2

公开(公告)日：2014-05-06

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：US08684691B2

公开(公告)日：2014-04-01

申请号：US13099521

申请日：2011-05-03

Applicant: Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

Inventor： Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

IPC: F01D5/20

CPC classification number: F01D5/20

Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Abstract translation: 公开了一种从压力侧肋和从涡轮叶片的尖端径向向外延伸的吸力侧肋形成的尖叫尖端。 压力和吸力侧肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力和吸力侧肋可以包括倒角的前缘，其中膜冷却孔具有位于其中的排气口。 膜冷却孔可以被配置为具有一个或多个锥形部分的扩散冷却孔，用于降低冷却流体的速度并增加对流表面的尺寸。