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51. 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。

52. 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。

53. 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。

54. 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。

55. 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。

56. 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。

57. 发明授权

US07510376B2 Skewed tip hole turbine blade 有权
标题翻译：倾斜尖端孔涡轮叶片
公开(公告)号：US07510376B2
公开(公告)日：2009-03-31
申请号：US11211391
申请日：2005-08-25
申请人： Ching-Pang Lee , Nicholas Charles Palmer , Kevin Lee Kirkeng
发明人： Ching-Pang Lee , Nicholas Charles Palmer , Kevin Lee Kirkeng
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D11/08 , F05D2240/307 , F05D2250/292 , F05D2250/38 , F05D2260/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor.
摘要翻译：涡轮机叶片包括具有延伸穿过其尖端底部的多个弓形尖端孔的中空翼型件，并且朝着从地板向外延伸的尖叫肋条倾斜。

58. 发明授权

US07503749B2 Turbine nozzle with trailing edge convection and film cooling 失效
标题翻译：涡轮喷嘴具有后缘对流和薄膜冷却
公开(公告)号：US07503749B2
公开(公告)日：2009-03-17
申请号：US11097474
申请日：2005-04-01
申请人： Ching-Pang Lee , Steven Robert Brassfield , Michael Joseph Danowski , Hardev Singh
发明人： Ching-Pang Lee , Steven Robert Brassfield , Michael Joseph Danowski , Hardev Singh
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/13 , F05D2250/184 , F05D2250/292 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.
摘要翻译：用于燃气涡轮发动机的翼型件具有在前缘和后缘之间延伸的相对的压力和吸力侧壁。翼型件包括在其间限定多个后缘槽的径向间隔开的纵向延伸的平台的阵列。每个后缘槽具有与翼型件的内部流体连通的入口和与后缘流体连通的出口。至少一个焊盘是锥形的，使得沿径向测量的焊盘的宽度从抽吸侧壁减小到压力侧壁。

59. 发明授权

US07487819B2 Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom 有权
标题翻译：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。

60. 发明授权

US07438520B2 Thermally compliant turbine shroud mounting assembly 有权
标题翻译：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。

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