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    Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly
    3.
    发明授权
    Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly 有权
    促进涡轮机罩组件优先分布复原薄膜冷却的方法和系统

    公开(公告)号：US07722315B2

    公开(公告)日：2010-05-25

    申请号：US11565253

    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： F01D25/14

    CPC分类号： F01D11/08 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49236

    摘要： A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.

    摘要翻译： 一种组装燃气涡轮发动机的方法包括将涡轮机罩组件联接在燃气涡轮发动机内。 涡轮机罩组件包括具有限定前表面和径向内表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的后表面和前表面之间限定间隙。 多个恢复的冷却开口通过前缘以相对于间隙的中心线和前表面和径向内表面之间的倾斜入口角定义，以将冷却流体引导通过前缘，以便于先导的优先冷却 边缘。

    Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
    4.
    发明授权
    Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies 失效
    整体涡轮喷嘴和护罩组件的回热冷却方法和系统

    公开(公告)号：US07665953B2

    公开(公告)日：2010-02-23

    申请号：US11565176

    申请日：2006-11-30

    申请人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

    发明人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

    IPC分类号： F01D25/12

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  Y02T50/671

    摘要： A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, and directing the cooling air in the gap through at least one cooling hole extending between the leading edge and the inner surface.

    摘要翻译： 提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。 该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在 涡轮喷嘴的外带和前缘。 该方法还包括将冷却空气引导到间隙中，以及通过在前缘和内表面之间延伸的至少一个冷却孔将间隙中的冷却空气引导。

    METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES
    5.
    发明申请
    METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES 失效
    用于冷却集成涡轮喷嘴和风力发电机组的方法和系统

    公开(公告)号：US20080131262A1

    公开(公告)日：2008-06-05

    申请号：US11565447

    申请日：2006-11-30

    申请人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

    发明人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

    IPC分类号： F01D5/08 ,  F01D25/12

    CPC分类号： F01D9/04 ,  F05D2240/80 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/671 ,  Y02T50/676

    摘要： A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.

    摘要翻译： 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘，以便薄膜冷却护罩段。

    Method and system to facilitate cooling turbine engines
    6.
    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

    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。

    Methods and system for cooling integral turbine shround assemblies
    7.
    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

    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。

    METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE SHROUD ASSEMBLIES
    8.
    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
    9.
    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。