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61. 发明申请

US20080152505A1 GAS TURBINE ENGINES INCLUDING MULTI-CURVE STATOR VANES AND METHODS OF ASSEMBLING THE SAME 有权
标题翻译：气体涡轮发动机，其中包括多级定子风扇及其组装方法
公开(公告)号：US20080152505A1
公开(公告)日：2008-06-26
申请号：US11615556
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F01D5/145 , F01D9/041 , F05D2240/301 , F05D2250/611 , F05D2250/71 , Y02T50/673
摘要： 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.
摘要翻译：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。

62. 发明申请

US20080135202A1 COMPOSITE CORE DIE, METHODS OF MANUFACTURE THEREOF AND ARTICLES MANUFACTURED THEREFROM 有权
标题翻译：复合芯套，其制造方法及其制造的制品
公开(公告)号：US20080135202A1
公开(公告)日：2008-06-12
申请号：US11567477
申请日：2006-12-06
申请人： Ching-Pang Lee , Hsin-Pang Wang , Ram Kumar Upadhyay , Paul Richard Myers , Marc Thomas Edgar , Thomas Donald Martyn , Eric Alan Estill
发明人： Ching-Pang Lee , Hsin-Pang Wang , Ram Kumar Upadhyay , Paul Richard Myers , Marc Thomas Edgar , Thomas Donald Martyn , Eric Alan Estill
IPC分类号： B22C9/10 , B28B7/34
CPC分类号： B22C9/10 , B22C9/101 , B22C9/103 , B28B7/342 , B28B7/346
摘要： 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.
摘要翻译：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。

63. 发明申请

US20080131265A1 Downstream plasma shielded film cooling 失效
标题翻译：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。

64. 发明申请

US20080131264A1 METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE SHROUD ASSEMBLIES 有权
标题翻译：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。

65. 发明申请

US20080131260A1 METHOD AND SYSTEM TO FACILITATE COOLING TURBINE ENGINES 有权
标题翻译：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。

66. 发明申请

US20080080968A1 METHODS AND APPARATUS FOR ASSEMBLING TURBINE ENGINES 有权
标题翻译：组装涡轮发动机的方法和装置
公开(公告)号：US20080080968A1
公开(公告)日：2008-04-03
申请号：US11538273
申请日：2006-10-03
申请人： Joseph Michael Guentert , Ching-Pang Lee
发明人： Joseph Michael Guentert , Ching-Pang Lee
IPC分类号： F01D25/26
CPC分类号： F01D25/246 , F01D11/005 , F05D2240/57
摘要： 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.
摘要翻译：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。

67. 发明申请

US20070134099A1 Damper cooled turbine blade 有权
标题翻译：阻尼器冷却涡轮叶片
公开(公告)号：US20070134099A1
公开(公告)日：2007-06-14
申请号：US11296910
申请日：2005-12-08
申请人： Ching-Pang Lee , Steven Brassfield , Jan Schilling
发明人： Ching-Pang Lee , Steven Brassfield , Jan Schilling
IPC分类号： F01D11/00
CPC分类号： F01D5/22 , F01D11/006 , F05D2240/81 , F05D2250/292 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10S416/50
摘要： 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.
摘要翻译：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。

68. 发明申请

US20070134089A1 Methods and apparatus for assembling turbine engines 有权
标题翻译：涡轮发动机组装方法及装置
公开(公告)号：US20070134089A1
公开(公告)日：2007-06-14
申请号：US11297699
申请日：2005-12-08
申请人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles
发明人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles
IPC分类号： F01D9/00
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F01D9/02 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： 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.
摘要翻译：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。

69. 发明申请

US20070104571A1 Methods and apparatus for assembling turbine engines 失效
标题翻译：涡轮发动机组装方法及装置
公开(公告)号：US20070104571A1
公开(公告)日：2007-05-10
申请号：US11271101
申请日：2005-11-10
申请人： Vincent Drerup , Harold Hansel , James Ketzer , Ching-Pang Lee
发明人： Vincent Drerup , Harold Hansel , James Ketzer , Ching-Pang Lee
IPC分类号： F01D9/00
CPC分类号： F02C7/28 , F01D11/005 , F05D2240/12 , F05D2260/30 , Y10T29/49297 , Y10T29/4932 , Y10T29/49323
摘要： A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one retainer tab to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.
摘要翻译：提供一种用于组装燃气涡轮发动机的方法。该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。该方法还包括形成至少一个保持器突片以从至少一个花键密封件的主体部分向外延伸，以及将至少一个花键密封件插入限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便于减少通过所述间隙的泄漏，使得至少一个保持器突片有助于将保持器突片保持在涡轮喷嘴槽内。

70. 发明申请

US20070059173A1 TURBINE AIRFOIL CURVED SQUEALER TIP WITH TIP SHELF 有权
标题翻译：涡轮机空气IL ED SQ SQ SQ。。。。。。。
公开(公告)号：US20070059173A1
公开(公告)日：2007-03-15
申请号：US11162434
申请日：2005-09-09
申请人： Ching-Pang Lee , Chander Prakash
发明人： Ching-Pang Lee , Chander Prakash
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/67
摘要： An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.
摘要翻译：用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。压力侧顶端壁的至少一部分从压力侧壁凹入以限定向外的顶端架，使得压力侧顶端壁和尖端架在其间限定槽。

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