公开(公告)号：US5326224A

公开(公告)日：1994-07-05

申请号：US801136

申请日：1991-12-02

Applicant: Ching-Pang Lee ,  Theodore T. Thomas, Jr. ,  Anne M. Isburgh

Inventor： Ching-Pang Lee ,  Theodore T. Thomas, Jr. ,  Anne M. Isburgh

IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

CPC classification number: F01D5/20 ,  F01D5/186 ,  Y02T50/676

Abstract: A jet engine component includes a body having a wall portion with an external surface exposed to hot gas flow and an internal surface exposed to a cooling air flow. The engine component incorporates an arrangement of cooling holes defined through the wall portion between the external and internal surfaces thereof to permit flow of cooling air from the hollow interior through the wall portion to the exterior of the component. Each cooling hole includes at least one flow inlet at the internal surface of the wall for receiving the cooling air flow, at least a pair of flow outlets at the external surface of the wall for discharging the cooling air flow, and at least a pair of flow branches extending through the wall portion and between the flow inlet and the flow outlets for permitting passage of the cooling air flow from the flow inlet to the flow outlets. In one V-shaped configuration, the flow branches merge and intersect with one another at the flow inlet. In another X-shaped configuration, there are a pair of flow inlets and the flow branches merge and intersect with one another at a location intermediate between and spaced from the flow inlets and outlets. The flow outlets are displaced preferably downstream of the flow inlet relative to the direction of gas flow past the external surface of the wall of the engine component.

Abstract translation: 喷气发动机部件包括具有暴露于热气流的外表面的壁部和暴露于冷却空气流的内表面的主体。 发动机部件包括在其外表面和内表面之间通过壁部分限定的冷却孔的布置，以允许冷却空气从中空内部流过壁部分到外部。 每个冷却孔包括用于接收冷却空气流的壁的内表面处的至少一个流入口，在壁的外表面处的至少一对流出口，用于排出冷却空气流，以及至少一对 流动分支延伸穿过壁部分并且在流入口和流出口之间，用于允许冷却空气流从流入口流到流出口。 在一个V形构造中，流动分支在流入口处相互合并并相互交叉。 在另一个X形构造中，存在一对流入口，并且流动分支在流入口和出口之间的中间和间隔开的位置处彼此合并和相交。 优选地，流动出口相对于通过发动机部件的壁的外表面的气流的方向在流入口的下游位移。

公开(公告)号：US10787911B2

公开(公告)日：2020-09-29

申请号：US16005535

申请日：2018-06-11

Applicant: Ching-Pang Lee ,  Benjamin Heneveld

Inventor： Ching-Pang Lee ,  Benjamin Heneveld

IPC: F01D5/18

Abstract: A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber. The cooling structure defines an interior cooling cavity and includes a plurality of cooling fluid outlet holes, at least one of which is in communication with a pressure side cooling circuit and at least one of which is in communication with a suction side cooling circuit. At least one of the pressure and suction side cooling circuits includes: a plurality of rows of airfoils, wherein radially adjacent airfoils within a row define segments of cooling channels. Outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent downstream row such that the cooling channels have a serpentine shape.

公开(公告)号：US09566642B2

公开(公告)日：2017-02-14

申请号：US13801483

申请日：2013-03-13

Applicant: Ching-Pang Lee ,  Hsin-Pang Wang ,  Ram Kumar Upadhyay ,  Paul Richard Myers ,  Marc Thomas Edgar ,  Thomas Donald Martyn ,  Eric Alan Estill

Inventor： Ching-Pang Lee ,  Hsin-Pang Wang ,  Ram Kumar Upadhyay ,  Paul Richard Myers ,  Marc Thomas Edgar ,  Thomas Donald Martyn ,  Eric Alan Estill

IPC: B22C9/10 ,  B28B7/34

CPC classification number: B22C9/10 ,  B22C9/101 ,  B22C9/103 ,  B28B7/342 ,  B28B7/346

Abstract: A composite core die includes a reusable core die; and a disposable core die. The disposable core die is in physical communication with the reusable core die and surfaces of communication between the disposable core die and the reusable core die serve as barriers to prevent the leakage of a slurry that is disposed in the composite core die.

Abstract translation: 复合芯模包括可重复使用的芯模; 和一次性芯片。 一次性芯模与可重复使用的芯模具物理连通，并且一次性芯模和可重复使用的芯模之间的连通表面用作屏障，以防止布置在复合芯模中的浆料的泄漏。

公开(公告)号：US09186757B2

公开(公告)日：2015-11-17

申请号：US13467298

申请日：2012-05-09

Applicant: Mrinal Munshi ,  Ching-Pang Lee ,  Benjamin P. Swanson ,  Petya M. Georgieva ,  James A. Morin

Inventor： Mrinal Munshi ,  Ching-Pang Lee ,  Benjamin P. Swanson ,  Petya M. Georgieva ,  James A. Morin

IPC: B23P6/00 ,  B23P19/04 ,  B23K9/04 ,  F01D5/00 ,  F01D5/18 ,  F01D5/20 ,  F01D11/14

CPC classification number: B23P6/002 ,  F01D5/005 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F01D11/14 ,  Y10T29/49318

Abstract: A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.

Abstract translation: 一种修复具有限定内腔宽度的径向延伸的外壁和叶片尖端的涡轮叶片的方法。 该方法包括去除叶片尖端的至少一部分以形成修复表面并且提供具有径向外侧的顶端帽，其外部宽度可以小于内部空腔宽度，并且具有径向内侧，内侧具有内部 宽度基本上等于或大于内腔宽度。 顶盖位于修复表面，并且使用延性焊接材料将尖端焊接到修复表面。 通过围绕尖端盖进行堆积焊接而形成盖周边部分，并且通过在盖周边部分上堆积焊接形成尖叫部分。

公开(公告)号：US20150184518A1

公开(公告)日：2015-07-02

申请号：US14140593

申请日：2013-12-26

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  B22C9/04 ,  B22D29/00 ,  B22C9/24 ,  B22D25/02 ,  B22C7/02 ,  B22C9/10

CPC classification number: F01D5/186 ,  B22C7/02 ,  B22C9/04 ,  B22C9/043 ,  B22C9/10 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2250/184

Abstract: A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs having wavy side edges that form a jagged edge As such, the nonlinear longitudinal axis of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance The nonlinear trailing edge exit slot may be formed using a ceramic core and investment casting.

Abstract translation: 公开了一种用于涡轮发动机的涡轮叶片的冷却系统，其具有由中央后缘冷却通道形成的后缘冷却通道和至少一个具有非线性纵向轴线的后缘出口槽。 后缘出口槽可以由具有形成锯齿状边缘的波浪形侧边缘的肋限定。因此，后缘出口槽的非线性纵向轴线减小有效流动面积，产生冲击和湍流以增加热传递并提供足够的机械 强度更好的铸造产量而不溢出以获得更好的性能非线性后缘出口槽可以使用陶瓷芯和熔模铸造形成。

公开(公告)号：US09068461B2

公开(公告)日：2015-06-30

申请号：US13212263

申请日：2011-08-18

Applicant: Vincent P. Laurello ,  Ching-Pang Lee

Inventor： Vincent P. Laurello ,  Ching-Pang Lee

IPC: F01D5/08

CPC classification number: F01D5/087

Abstract: A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids entering the inlet orifice in the rotor, thereby availing the cooling system to the efficiencies inherent in pre-swirling the cooling fluids to a velocity that is greater than a rotational velocity of the turbine rotor body. As such, the system is capable of taking advantage of the additional temperature and work benefits associated with using the pre-swirled cooling fluids having a rotational speed greater than the turbine rotor body.

Abstract translation: 一种涡轮转子体，具有至少一个入口孔，其与预旋系统流体连通，使得入口孔接收来自预涡流系统的冷却流体。 入口孔口可以被配置为减小与进入转子中的入口孔口的冷却流体相关联的相对速度损失，从而将冷却系统利用到将冷却流体预旋转的固有效率大于旋转速度 的涡轮转子体。 因此，该系统能够利用与使用具有大于涡轮转子体的转速的预旋涡冷却流体相关联的附加温度和工作效益。

公开(公告)号：US09062557B2

公开(公告)日：2015-06-23

申请号：US13226547

申请日：2011-09-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Abdullatif M. Chehab ,  Gm Salam Azad ,  Shantanu P. Mhetras ,  Manjit Shivanand ,  Vincent P. Laurello ,  Christopher Rawlings

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Abdullatif M. Chehab ,  Gm Salam Azad ,  Shantanu P. Mhetras ,  Manjit Shivanand ,  Vincent P. Laurello ,  Christopher Rawlings

IPC: F01D1/02 ,  F01D11/00 ,  F01D11/04

CPC classification number: F01D11/001 ,  F01D11/04

Abstract: A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).

Abstract translation: 一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。 密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。 转子凸缘（41i，41o）从转子盘（9-1）延伸。 内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。 一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。 内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。 入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。

公开(公告)号：US09039371B2

公开(公告)日：2015-05-26

申请号：US14068070

申请日：2013-10-31

Applicant: Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

Inventor： Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/187 ,  F01D9/02 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/2212

Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Abstract translation: 一种燃气涡轮发动机部件，包括：具有内表面（34）的压力侧（12）; 吸入侧（14），其具有内表面（36）; 后缘部分（30）; 以及设置在后缘部分（30）中的多个吸力侧和压力侧冲击孔（24）。 每个吸入侧冲击孔构造成将锐角（52）的冲击射流（48）引导到目标区域（60）上，所述目标区域包围形成的人字形布置（120）内的人字形（122）的尖端（140） 在吸力侧内表面。 每个压力侧冲击孔构造成将冲击射流以锐角引导到细长的目标区域上，所述细长目标区域包含形成在压力侧内表面中的人字形布置中的人字形尖端。

公开(公告)号：US08973372B2

公开(公告)日：2015-03-10

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: F01D25/12 ,  F02C3/30 ,  F02C3/04 ,  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：US08944763B2

公开(公告)日：2015-02-03

申请号：US13212282

申请日：2011-08-18

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/08

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。