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1. 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。

2. 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。

3. 发明授权

US07665953B2 Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies 失效
标题翻译：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。

4. 发明申请

US20080206042A1 METHODS AND SYSTEM FOR RECUPERATED CIRCUMFERENTIAL COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES 有权
标题翻译：整体涡轮喷嘴和风力发电机组的回路循环冷却方法与系统
公开(公告)号：US20080206042A1
公开(公告)日：2008-08-28
申请号：US11565180
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： F04D31/00
CPC分类号： F01D5/143 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
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, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum 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，将冷却空气周向地混合在限定在前缘内的增压室中，以将冷却空气基本上均匀地分布在整个间隙中，并且将空气中的冷却空气引导通过形成的至少一个冷却孔在气室和内表面之间。

5. 发明授权

US07604453B2 Methods and system for recuperated circumferential cooling of integral turbine nozzle and shroud assemblies 有权
标题翻译：整体涡轮喷嘴和护罩组件的周期性冷却方法和系统
公开(公告)号：US07604453B2
公开(公告)日：2009-10-20
申请号：US11565180
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： F01D5/143 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
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, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum 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，将冷却空气周向地混合在限定在前缘内的增压室中，以将冷却空气基本上均匀地分布在整个间隙中，并且将空气中的冷却空气引导通过形成的至少一个冷却孔在气室和内表面之间。

6. 发明申请

US20080131259A1 METHODS AND SYSTEM FOR RECUPERATED COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES 失效
标题翻译：整体涡轮喷嘴和风力发电机组的回收冷却方法与系统
公开(公告)号：US20080131259A1
公开(公告)日：2008-06-05
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。

7. 发明授权

US08147192B2 Dual stage turbine shroud 有权
标题翻译：双级涡轮罩
公开(公告)号：US08147192B2
公开(公告)日：2012-04-03
申请号：US12233847
申请日：2008-09-19
申请人： Daniel Vern Jones , James Harvey Laflen , Richard William Albrecht , Dustin Alfred Placke , Ching-Pang Lee
发明人： Daniel Vern Jones , James Harvey Laflen , Richard William Albrecht , Dustin Alfred Placke , Ching-Pang Lee
IPC分类号： F01D5/20 , F01D11/08
CPC分类号： F01D25/246 , F01D11/24 , F05D2240/11 , Y02T50/671
摘要： A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.
摘要翻译：涡轮机罩包括具有弓形面板的护罩悬挂器，三个内钩从该拱形板向内延伸，两个外钩从其中向外延伸。两个外钩影响护罩的静态结构。

8. 发明申请

US20100074745A1 DUAL STAGE TURBINE SHROUD 有权
标题翻译：双级涡轮SHROUD
公开(公告)号：US20100074745A1
公开(公告)日：2010-03-25
申请号：US12233847
申请日：2008-09-19
申请人： Daniel Vern Jones , James Harvey Laflen , Richard William Albrecht , Dustin Alfred Placke , Ching-Pang Lee
发明人： Daniel Vern Jones , James Harvey Laflen , Richard William Albrecht , Dustin Alfred Placke , Ching-Pang Lee
IPC分类号： F01D9/04
CPC分类号： F01D25/246 , F01D11/24 , F05D2240/11 , Y02T50/671
摘要： A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.
摘要翻译：涡轮机罩包括具有弓形面板的护罩悬挂器，三个内钩从该拱形板向内延伸，两个外钩从其中向外延伸。两个外钩影响护罩的静态结构。

9. 发明申请

US20080131262A1 METHODS AND SYSTEM FOR COOLING INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES 失效
标题翻译：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。

10. 发明授权

US07740442B2 Methods and system for cooling integral turbine nozzle and shroud assemblies 失效
标题翻译：冷却整体涡轮喷嘴和护罩组件的方法和系统
公开(公告)号：US07740442B2
公开(公告)日：2010-06-22
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： 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。

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