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    Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom
    64.
    发明授权
    Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom 有权
    一次性薄壁芯模，其制造方法和由其制造的制品

    公开(公告)号：US07487819B2

    公开(公告)日：2009-02-10

    申请号：US11609117

    申请日：2006-12-11

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

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

    IPC分类号： B22C9/04 ,  B22C9/10

    CPC分类号： B22C9/04 ,  B22C9/10 ,  C04B35/6269 ,  C04B2235/6026 ,  C04B2235/6028

    摘要： 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.

    摘要翻译： 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。

    Thermally compliant turbine shroud mounting assembly
    65.
    发明授权
    Thermally compliant turbine shroud mounting assembly 有权
    符合标准的涡轮机罩安装组件

    公开(公告)号：US07438520B2

    公开(公告)日：2008-10-21

    申请号：US11161516

    申请日：2005-08-06

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

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

    IPC分类号： F01D11/08

    CPC分类号： F01D11/08 ,  F01D11/12 ,  F01D11/122

    摘要： 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.

    摘要翻译： 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。

    Downstream plasma shielded film cooling
    68.
    发明申请
    Downstream plasma shielded film cooling 失效
    下游等离子屏蔽膜冷却

    公开(公告)号：US20080131265A1

    公开(公告)日：2008-06-05

    申请号：US11606853

    申请日：2006-11-30

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

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

    IPC分类号： F01D5/18 ,  F01D25/12

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

    摘要： 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.

    摘要翻译： 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。

    METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE SHROUD ASSEMBLIES
    69.
    发明申请
    METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE SHROUD ASSEMBLIES 有权
    用于冷却整体涡轮机组件的方法和系统

    公开(公告)号：US20080131264A1

    公开(公告)日：2008-06-05

    申请号：US11565387

    申请日：2006-11-30

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

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

    IPC分类号： F01D25/14 ,  F01D25/28

    CPC分类号： F01D11/24 ,  F01D25/246 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

    摘要： 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.

    摘要翻译： 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。

    METHOD AND SYSTEM TO FACILITATE COOLING TURBINE ENGINES
    70.
    发明申请
    METHOD AND SYSTEM TO FACILITATE COOLING TURBINE ENGINES 有权
    冷却涡轮发动机的方法和系统

    公开(公告)号：US20080131260A1

    公开(公告)日：2008-06-05

    申请号：US11565229

    申请日：2006-11-30

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

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

    IPC分类号： F01D25/12

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

    摘要： 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.

    摘要翻译： 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。