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41. 发明授权

US07870719B2 Plasma enhanced rapidly expanded gas turbine engine transition duct 有权
标题翻译：等离子体增强了快速扩大的燃气轮机发动机过渡管道
公开(公告)号：US07870719B2
公开(公告)日：2011-01-18
申请号：US11580788
申请日：2006-10-13
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
IPC分类号： F02H1/00
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F05D2260/221 , F05D2270/172 , Y02T50/671 , Y02T50/673 , Y02T50/675
摘要： A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.
摘要翻译：等离子体增强的快速扩张的管道系统包括燃气涡轮发动机涡轮机间过渡管道，其具有在管道入口和管道出口之间轴向延伸的径向间隔开的锥形内部和外部管道壁。锥形等离子体发生器沿着外管道壁产生锥形等离子体。锥形等离子体发生器的示例性实施例安装到外部管道壁并且包括由电介质材料隔开的径向内部和外部电极。介电材料设置在外管道壁的径向向内的表面内的锥形槽内。 AC电源连接到电极以向电极提供高电压AC电位。

42. 发明申请

US20100284795A1 Plasma Clearance Controlled Compressor 审中-公开
标题翻译：等离子体间隙控制压缩机
公开(公告)号：US20100284795A1
公开(公告)日：2010-11-11
申请号：US11966309
申请日：2007-12-28
申请人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
发明人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
IPC分类号： F01D11/08
CPC分类号： F01D11/20 , F05D2270/172
摘要： A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.
摘要翻译：公开了一种用于压缩机的等离子体泄漏流量控制系统，包括圆周排的压缩机叶片，围绕叶片尖端的环形壳体，位于与叶片的尖端径向分开的位置以及至少一个环形等离子体发生器，其位于环形套管。环形等离子体发生器包括由电介质材料隔开的内电极和外电极。具有等离子体泄漏流量控制系统的燃气涡轮发动机还包括发动机控制系统，其控制环形等离子体发生器的操作，使得可以改变叶片尖端泄漏流。

43. 发明授权

US07785067B2 Method and system to facilitate cooling turbine engines 有权
标题翻译：便于冷却涡轮发动机的方法和系统
公开(公告)号：US07785067B2
公开(公告)日：2010-08-31
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。

44. 发明授权

US07758306B2 Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
标题翻译：用于燃气涡轮发动机的涡轮组件及其制造方法
公开(公告)号：US07758306B2
公开(公告)日：2010-07-20
申请号：US11615514
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： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49236
摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.
摘要翻译：一种用于燃气涡轮发动机的涡轮组件。涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

45. 发明授权

US07740444B2 Methods and system for cooling integral turbine shround assemblies 有权
标题翻译：冷却整体涡轮机组件的方法和系统
公开(公告)号：US07740444B2
公开(公告)日：2010-06-22
申请号：US11565387
申请日：2006-11-30
申请人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
发明人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
IPC分类号： F01D25/12
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。

46. 发明申请

US20100143139A1 BANKED PLATFORM TURBINE BLADE 有权
标题翻译： BANKED平台涡轮叶片
公开(公告)号：US20100143139A1
公开(公告)日：2010-06-10
申请号：US12330783
申请日：2008-12-09
申请人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
发明人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
IPC分类号： F01D5/22 , F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。平台的高度是从靠近翼型的压力侧的一个堤岸到从翼型前缘的后面开始的槽。

47. 发明申请

US20090324422A1 Cascade tip baffle airfoil 有权
标题翻译：级联顶端挡板翼型
公开(公告)号：US20090324422A1
公开(公告)日：2009-12-31
申请号：US11507120
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
摘要翻译：涡轮叶片包括具有沿相对的压力和吸力侧延伸的第一和第二肋的翼型端。肋从尖端底部向外延伸并且在相对的前缘和后缘处连接在一起。级联顶端挡板将尖端底部上方的两个肋横向地桥接在尖端的最大宽度的前方，以将端部弦状地分隔成挡板相对侧上的相应的尖端口。

48. 发明授权

US07591070B2 Turbine blade tip squealer and rebuild method 失效
标题翻译：涡轮叶尖尖叫声和重建方法
公开(公告)号：US07591070B2
公开(公告)日：2009-09-22
申请号：US11766488
申请日：2007-06-21
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： B23P15/02 , F01D5/20
CPC分类号： B23P6/007 , F01D5/005 , F01D5/20 , F05D2260/202 , Y10T29/49318 , Y10T29/49337 , Y10T29/49339 , Y10T29/49341 , Y10T29/49728 , Y10T29/53091
摘要： A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.
摘要翻译：具有尖端喷嘴的涡轮机叶片和用于重建用于燃气涡轮发动机的涡轮机叶片的方法。叶片类型包括具有限定内部空隙并且在前缘和后缘处连接的第一和第二间隔开的侧壁的翼型件。所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到用于引导燃烧气体的尖端帽，以及尖叫尖端，其包括从所述尖端帽向外延伸的至少一个尖端肋。该方法包括以下步骤：从顶盖移除包括至少一个肋尖端的尖叫尖端，并将新材料添加到尖端盖以用作新的尖叫尖端。在翼缘的前缘和后缘之间的新材料中形成多个间隔开的凹口。在与翼型件的内部空隙连通的每个凹口中形成至少一个孔，用于从翼型的内部空间引导冷却空气，从而形成尖叫尖端。

49. 发明申请

US20090169361A1 COOLED TURBINE NOZZLE SEGMENT 审中-公开
标题翻译：冷却涡轮喷嘴部分
公开(公告)号：US20090169361A1
公开(公告)日：2009-07-02
申请号：US11967190
申请日：2007-12-29
申请人： Michael Scott Cole , James Herbert Deines , Ching-Pang Lee
发明人： Michael Scott Cole , James Herbert Deines , Ching-Pang Lee
IPC分类号： F01D5/08 , F01D5/14
CPC分类号： F01D9/042 , F01D5/082 , F05B2260/301 , F05D2230/64 , F05D2230/90 , Y02T50/67 , Y02T50/676 , Y02T50/6765
摘要： A turbine nozzle segment may have a band having a flange extending radially from a non-flowpath side and an aft end. A plurality of airfoils may extend radially from a flowpath side of the band and may have trailing edges. A plurality of cooling holes may be disposed in the flange and directed at the aft end between the trailing edges.
摘要翻译：涡轮喷嘴段可以具有带子，其具有从非流动路径侧和后端径向延伸的凸缘。多个翼型件可以从带的流路侧径向延伸并且可以具有后缘。多个冷却孔可以设置在凸缘中并且指向后缘之间的后端。

50. 发明申请

US20090165275A1 METHOD FOR REPAIRING A COOLED TURBINE NOZZLE SEGMENT 审中-公开
标题翻译：修复冷却涡轮喷嘴部分的方法
公开(公告)号：US20090165275A1
公开(公告)日：2009-07-02
申请号：US11967193
申请日：2007-12-29
申请人： Michael Scott Cole , James Herbert Deines , Ching-Pang Lee
发明人： Michael Scott Cole , James Herbert Deines , Ching-Pang Lee
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , B23P6/002 , F01D9/042 , F05D2230/10 , F05D2230/12 , F05D2230/13 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y02T50/6765 , Y10T29/49719
摘要： A method for repairing a turbine nozzle segment having a band and a plurality of airfoils, where the band has a flange is described. The method includes the steps of repairing a damaged area on the turbine nozzle segment and drilling a plurality of cooling holes in the flange.
摘要翻译：描述了具有带和多个翼型件的涡轮喷嘴段的修复方法，其中带具有凸缘。该方法包括修复涡轮喷嘴段上的损坏区域并在凸缘中钻多个冷却孔的步骤。

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