公开(公告)号：US09334741B2

公开(公告)日：2016-05-10

申请号：US12765004

申请日：2010-04-22

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

IPC: B32B3/10 ,  B32B3/12 ,  F01D5/18

CPC classification number: F01D5/182 ,  B33Y80/00 ,  F01D5/183 ,  F01D5/184 ,  F05D2230/22 ,  F05D2230/90 ,  F05D2250/18 ,  F05D2250/185 ,  F05D2250/28 ,  F05D2250/30 ,  F05D2260/203 ,  F05D2260/221 ,  Y10T428/24273

Abstract: A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).

Abstract translation: 具有非随机空隙（26A，26B，28B，30B）的层（A，B，C，D，E）的壁结构（32,42,68,70,80），其互连以在 所述壁的内部（21）和外表面（23）用于所述壁的蒸发冷却。 通过壁的冷却剂流（38）可以通过冷却剂出口（31）和/或通道内的限制来计量，以使冷却剂需求最小化。 口袋（44）可以形成在隔热壁的外表面上（46）。 层可以通过层压，添加剂制造或铸造形成。 层几何形状包括具有不同重叠空白图案（42），3-D网格结构（70）和偏置华夫饼结构（80）的交替层（A，B，C）。

公开(公告)号：US09206700B2

公开(公告)日：2015-12-08

申请号：US14062925

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: F01D25/24 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D25/246 ,  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 for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

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，用于为发动机部分中的一排叶片提供结构支撑，后钩，前壁和强背板 。 后钩从主体部分的后侧延伸并且联接到外部发动机壳体，用于在发动机部分中结构地支撑支撑环。 前壁从主体部分的前侧大致径向向外延伸。 强后背板在前壁和后钩之间跨越，并且在发动机操作期间实现前壁和后钩之间的动态位移的减小。

公开(公告)号：US09181819B2

公开(公告)日：2015-11-10

申请号：US12813624

申请日：2010-06-11

Applicant: Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

Inventor： Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

IPC: F01D5/18 ,  F01D25/12

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：US09120144B2

公开(公告)日：2015-09-01

申请号：US13760290

申请日：2013-02-06

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: B22C9/10 ,  F01D5/14 ,  F01D5/18

CPC classification number: B22C9/10 ,  F01D5/141 ,  F01D5/187

Abstract: A casting core (200) for a twisted gas turbine engine blade, including: an airfoil portion (202) having: an airfoil base end (208), an airfoil tip end (210), a concave side exterior surface (212), a convex side exterior surface (214), a leading edge (204), and a trailing edge (206). The airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end. The airfoil portion includes a first void (220) between the concave side exterior surface and the convex side exterior surface and extending radially to define the shape of a rib of an airfoil to be cast around the core. A first leading edge surface and a first trailing edge surface of the void are twisted from the airfoil base end to the airfoil tip end.

Abstract translation: 一种用于扭转燃气涡轮发动机叶片的铸造芯（200），包括：机翼部分（202），其具有：翼型基端（208），翼型末端（210），凹侧外表面（212）， 凸起侧外表面（214），前缘（204）和后缘（206）。 翼型部分从翼型件底端到翼型件末端的径向扭转。 翼型部分包括在凹侧外表面和凸侧外表面之间的第一空隙（220），并且径向延伸以限定要围绕芯体铸造的翼型肋的形状。 空隙的第一前缘表面和第一后缘表面从翼型件基端扭转到翼型件末端。

公开(公告)号：US20150122446A1

公开(公告)日：2015-05-07

申请号：US14073922

申请日：2013-11-07

Applicant: Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. Um ,  Gm Salam Azad

Inventor： Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. Um ,  Gm Salam Azad

IPC: B22D25/02 ,  B22C9/10

CPC classification number: B22C9/10 ,  B22C7/02 ,  B22C7/06 ,  B22C9/04

Abstract: An investment casting method for a cast ceramic core (110), including an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50) and an integral shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.

Abstract translation: 一种用于铸造陶瓷芯（110）的熔模铸造方法，包括形成为限定叶片段（50）的翼型件（52）的内表面（56）和整体壳体部分（122）的翼型部分（116） 具有形成为限定叶片段的护罩（62）的后侧表面（68）的后侧成形表面（120）。 后侧成形表面具有较高的仰角（132）和较低的高度（134）。 较高的高度与翼面部分的最近点（138）分开，较低的高度。 翼型部分和壳体部分在单次铸造过程中作为整体式铸造。

公开(公告)号：US20150118034A1

公开(公告)日：2015-04-30

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：US09017025B2

公开(公告)日：2015-04-28

申请号：US13092303

申请日：2011-04-22

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2210/33 ,  F05D2250/185 ,  F05D2260/2212

Abstract: A serpentine cooling circuit (AFT) in a turbine airfoil (34A) starting from a radial feed channel (C1), and progressing axially (65) in alternating tangential directions through interconnected channels (C1, C2, C3) formed between partitions (T1, T2, J1). At least one of the partitions (T1, T2) has a T-shaped transverse section, with a base portion (67) extending from a suction or pressure side wall (64, 62) of the airfoil, and a crossing portion (68, 69) parallel to, and not directly attached to, the opposite pressure or suction side wall (62, 64). Each crossing portion bounds a near-wall passage (N1, N2) adjacent to the opposite pressure or suction side wall (62, 64). Each near-wall passage may have a smaller flow aperture area than one, or each, of two adjacent connected channels (C1, C2, C3). The serpentine circuit (AFT) may follow a forward cooling circuit (FWD) in the airfoil (34A).

Abstract translation: 涡轮机翼型（34A）中的蛇形冷却回路（AFT），其从径向进料通道（C1）开始，并且沿交替的切线方向通过形成在分隔件（T1，C2）之间的互连通道（C1，C2，C3） T2，J1）。 至少一个隔板（T1，T2）具有T形横截面，其中从翼型件的吸力或压力侧壁（64,62）延伸的基部（67）和交叉部分 69）平行于并且不直接附接到相对的压力或吸力侧壁（62,64）。 每个交叉部分限定与相对的压力或吸力侧壁（62,64）相邻的近壁通道（N1，N2）。 每个近壁通道可以具有比两个相邻连接的通道（C1，C2，C3）中的一个或每个通道更小的流通孔面积。 蛇形回路（AFT）可以跟随机翼（34A）中的向前冷却回路（FWD）。

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：US08936068B2

公开(公告)日：2015-01-20

申请号：US13087428

申请日：2011-04-15

Applicant: Ching-Pang Lee ,  Gary B. Merrill ,  Andrew J. Burns

Inventor： Ching-Pang Lee ,  Gary B. Merrill ,  Andrew J. Burns

IPC: B22C7/02 ,  B22C9/04 ,  B22C9/10

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.

公开(公告)号：US08926283B2

公开(公告)日：2015-01-06

申请号：US13688411

申请日：2012-11-29

Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Eric Schroeder

Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Eric Schroeder

IPC: F01D11/00 ,  F01D5/14 ,  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。