公开(公告)号：US07487819B2

公开(公告)日：2009-02-10

申请号：US11609117

申请日：2006-12-11

Applicant: Hsin-Pang Wang ,  Marc Thomas Edgar ,  John Thomas Leman ,  Ching-Pang Lee ,  Eric Alan Estill

Inventor： Hsin-Pang Wang ,  Marc Thomas Edgar ,  John Thomas Leman ,  Ching-Pang Lee ,  Eric Alan Estill

IPC: B22C9/04 ,  B22C9/10

CPC classification number: B22C9/04 ,  B22C9/10 ,  C04B35/6269 ,  C04B2235/6026 ,  C04B2235/6028

Abstract: Disclosed herein is a method comprising injecting into a thin wall disposable core die a slurry having a viscosity of about 1 to about 1,000 Pascal-seconds at room temperature when tested at a shear rate of up to 70 seconds−1 and a flow index of less than 0.6 at a pressure of up to about 7 kilograms-force per square centimeter; wherein the thin wall disposable core die has an average wall thickness of about 1.5 to about 10 millimeters; curing the slurry to form a cured ceramic core; removing the thin wall disposable core die from the cured ceramic core; and firing the cured ceramic core to form a solidified ceramic core.

Abstract translation: 本文公开了一种方法，包括在室温下将剪切速率高达70秒-1并且流动指数较小的样品在室温下注入具有约1至约1,000帕斯卡 - 秒的粘度的薄壁一次性芯模中 在0.6立方厘米的压力下，最高可达约7千克力; 其中所述薄壁一次性芯模的平均壁厚为约1.5至约10毫米; 固化浆料以形成固化的陶瓷芯; 从固化的陶瓷芯上去除薄壁一次性芯模; 并烧结固化的陶瓷芯以形成凝固的陶瓷芯。

公开(公告)号：US07438520B2

公开(公告)日：2008-10-21

申请号：US11161516

申请日：2005-08-06

Applicant: Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

Inventor： Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F01D11/12 ,  F01D11/122

Abstract: A shroud assembly is provided for a gas turbine engine that has a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes: at least one arcuate shroud segment adapted to surround a row of rotating turbine blades which has an arcuate, axially extending mounting flange; a shroud hanger having an arcuate, axially-extending hook disposed in mating relationship to the mounting flange; and an arcuate C-clip having inner and outer arms overlapping the hook and the mounting flange. The curvatures of the mounting flange and the inner arm of the C-clip are selected so as to define a matched interface therebetween. Their curvatures are substantially greater that the curvature of the hook.

Abstract translation: 提供一种用于燃气涡轮发动机的护罩组件，其具有基本上大于其冷组装状态下的热操作状态的温度。 所述护罩组件包括：至少一个弧形护罩段，其适于包围一排旋转的涡轮叶片，所述旋转涡轮叶片具有弓形的轴向延伸的安装凸缘; 护罩悬挂器具有与安装凸缘成配合关系设置的弓形的轴向延伸的钩; 以及弓形C形夹具，其内外臂与钩和安装法兰重叠。 选择安装法兰和C形夹的内臂的曲率，以便在它们之间限定一个匹配的接口。 它们的曲率大大地大于钩的曲率。

公开(公告)号：US20080152505A1

公开(公告)日：2008-06-26

申请号：US11615556

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D9/00

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/301 ,  F05D2250/611 ,  F05D2250/71 ,  Y02T50/673

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract translation: 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。

公开(公告)号：US20080135202A1

公开(公告)日：2008-06-12

申请号：US11567477

申请日：2006-12-06

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: Disclosed herein is a composite core die comprising a reusable core die; and a disposable core die; wherein the disposable core die is in physical communication with the reusable core die; and further wherein 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: 本文公开了一种复合芯模，其包括可重复使用的芯模; 和一次性芯模; 其中所述一次性芯管芯与所述可重复使用的芯管芯物理连通; 并且其中一次性芯模和可重复使用的芯模之间的连通表面用作阻挡物以防止布置在复合芯模中的浆料的泄漏。

公开(公告)号：US20080131265A1

公开(公告)日：2008-06-05

申请号：US11606853

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/172 ,  F15D1/12 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S165/903 ,  Y10S415/914

Abstract: An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located downstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the downstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.

Abstract translation: 下游等离子体边界层屏蔽系统包括薄膜冷却孔，该薄膜冷却孔通过具有冷和热表面的壁布置，并且在下游方向上从壁的冷表面到壁的外部热表面成角度。 位于膜冷却孔下游的等离子体发生器用于产生在膜冷却孔的下游延伸的等离子体。 每个等离子体发生器包括由设置在外部热表面中的凹槽内的电介质材料分开的内部和外部电极。 该壁可以是中空翼型件或环形燃烧器或排气衬套的一部分。 一种用于操作下游等离子体边界层屏蔽系统的方法包括形成沿着下游方向延伸的等离子体沿着壁的外部热表面的膜冷却孔。 该方法还可以包括以等稳态或不稳定模式操作等离子体发生器。

公开(公告)号：US20080131264A1

公开(公告)日：2008-06-05

申请号：US11565387

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  James Harvey Laflen ,  Dustrin Alfred Placke ,  George Elliott Moore ,  Katherine Jaynetorrence Andersen ,  Daniel Verner Jones

Inventor： Ching-Pang Lee ,  James Harvey Laflen ,  Dustrin Alfred Placke ,  George Elliott Moore ,  Katherine Jaynetorrence Andersen ,  Daniel Verner Jones

IPC: F01D25/14 ,  F01D25/28

CPC classification number: F01D11/24 ,  F01D25/246 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

Abstract: A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly. Cooling air is metered through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support while substantially preventing cooling air from entering an inactive convection cooling zone positioned radially outwardly from the at least one active convection cooling zone and defined between the shroud support and the shroud ring structure and between the midsection position control ring and the aft position control ring.

Abstract translation: 一种用于冷却涡轮机护罩组件的方法包括提供一种涡轮机护罩组件，其包括具有前缘，后缘和在其间限定的中部的护罩段。 护罩支撑件周向地跨越并支撑护罩段。 护罩支撑件包括联接到前缘的前悬挂器，联接到中部的中间吊架和耦合到后缘的后挂架。 环形护罩环结构包括连接到中间悬挂架的中央位置控制环和联接到后悬挂架的后部位置控制环。 从位于涡轮机罩组件上游的压缩机抽出冷却空气。 冷却空气通过护罩支撑件计量直接仅限于限定在护罩区段和护罩支撑件之间的至少一个主动对流冷却区域，同时基本上防止冷却空气进入从至少一个主动对流冷却器径向向外定位的非活动对流冷却区域 并且限定在护罩支撑件和护罩环结构之间以及中间位置控制环和后部位置控制环之间。

公开(公告)号：US20080131260A1

公开(公告)日：2008-06-05

申请号：US11565229

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D9/04 ,  F01D11/08 ,  F01D11/24 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/314 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49236

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.

Abstract translation: 提供一种组装燃气涡轮发动机的方法。 该方法包括联接燃气涡轮发动机内的至少一个涡轮喷嘴段。 至少一个涡轮喷嘴段包括在内带和外带之间延伸的至少一个翼型叶片，其包括后翼缘和径向内表面。 该方法还包括将至少一个涡轮机护罩段联接到至少一个涡轮喷嘴段的下游，其中至少一个涡轮机护罩段包括前缘和径向内表面，并且将冷却流体源与 至少一个涡轮喷嘴段，使得被引导到每个涡轮喷嘴外带后缘的冷却流体朝向至少一个涡轮机护罩段的前缘以倾斜的排出角度引导。

公开(公告)号：US20080080968A1

公开(公告)日：2008-04-03

申请号：US11538273

申请日：2006-10-03

Applicant: Joseph Michael Guentert ,  Ching-Pang Lee

Inventor： Joseph Michael Guentert ,  Ching-Pang Lee

IPC: F01D25/26

CPC classification number: F01D25/246 ,  F01D11/005 ,  F05D2240/57

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括提供包括外带和内带的涡轮喷嘴，其中每个带包括前缘，后缘和在其间延伸的本体。 外带和内带中的至少一个具有从其向外延伸的至少一个径向突片。 该方法还包括在从外带和内带延伸的至少一个径向突片和外带和内带的相应前缘之间联接至少一个密封件。 该方法还包括将至少一个非平面密封支撑件定位在密封件的至少一部分上。

公开(公告)号：US20070134099A1

公开(公告)日：2007-06-14

申请号：US11296910

申请日：2005-12-08

Applicant: Ching-Pang Lee ,  Steven Brassfield ,  Jan Schilling

Inventor： Ching-Pang Lee ,  Steven Brassfield ,  Jan Schilling

IPC: F01D11/00

CPC classification number: F01D5/22 ,  F01D11/006 ,  F05D2240/81 ,  F05D2250/292 ,  F05D2250/314 ,  Y02T50/671 ,  Y02T50/676 ,  Y10S416/50

Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.

Abstract translation: 涡轮机叶片包括整体连接在一起的翼型件，平台，柄和燕尾榫。 冷却室位于平台下方并具有从柄部向外露出的入口。 阻尼器座圈围绕入口并且凹陷在平台下方，用于接收振动阻尼器以密封地封闭穿过入口的腔室。

公开(公告)号：US20070134089A1

公开(公告)日：2007-06-14

申请号：US11297699

申请日：2005-12-08

Applicant: Ching-Pang Lee ,  Joseph Guentert ,  Wenfeng Lu ,  Mitchell Iles

Inventor： Ching-Pang Lee ,  Joseph Guentert ,  Wenfeng Lu ,  Mitchell Iles

IPC: F01D9/00

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

Abstract translation: 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，该涡轮喷嘴包括内带，外带，在内带和外带之间延伸的至少一个叶片，以及在至少一个叶片和至少一个叶片之间延伸的至少一个前缘圆角 内部和外部带，其中所述至少一个叶片的前缘在所述内部和外部带的前缘的下游，以及将所述涡轮喷嘴连接在所述燃气涡轮发动机内，使得所述前缘圆角被配置为有助于最小化涡旋 沿着与内带和外带中的至少一个相邻的叶片前缘的形成。