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    Method and system to facilitate cooling turbine engines
    31.
    发明授权
    Method and system to facilitate cooling turbine engines 有权
    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

    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。

    Turbine assembly for a gas turbine engine and method of manufacturing the same
    32.
    发明授权
    Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
    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

    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: F01D1/02

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

    Abstract: 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.

    Abstract translation: 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。

    Methods and system for cooling integral turbine shround assemblies
    33.
    发明授权
    Methods and system for cooling integral turbine shround assemblies 有权
    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

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

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

    IPC: F01D25/12

    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。

    Cascade tip baffle airfoil
    35.
    发明申请
    Cascade tip baffle airfoil 有权
    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

    Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    IPC: F01D5/18

    CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: 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.

    Abstract translation: 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。

    Turbine blade tip squealer and rebuild method
    36.
    发明授权
    Turbine blade tip squealer and rebuild method 失效
    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

    Applicant: Ching-Pang Lee

    Inventor： Ching-Pang Lee

    IPC: B23P15/02 ,  F01D5/20

    CPC classification number: B23P6/007 ,  F01D5/005 ,  F01D5/20 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49728 ,  Y10T29/53091

    Abstract: 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.

    Abstract translation: 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。

    Turbine nozzle with trailing edge convection and film cooling
    40.
    发明授权
    Turbine nozzle with trailing edge convection and film cooling 失效
    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

    Applicant: Ching-Pang Lee ,  Steven Robert Brassfield ,  Michael Joseph Danowski ,  Hardev Singh

    Inventor： Ching-Pang Lee ,  Steven Robert Brassfield ,  Michael Joseph Danowski ,  Hardev Singh

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2250/13 ,  F05D2250/184 ,  F05D2250/292 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    Abstract: 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.

    Abstract translation: 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。

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