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1. 发明申请

US20120201674A1 COOLING MODULE DESIGN AND METHOD FOR COOLING COMPONENTS OF A GAS TURBINE SYSTEM 有权
标题翻译：用于冷却气体涡轮机组件的冷却模块设计和方法
公开(公告)号：US20120201674A1
公开(公告)日：2012-08-09
申请号：US13023716
申请日：2011-02-09
申请人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
发明人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
IPC分类号： F01D5/18
CPC分类号： F01D5/184 , F01D5/186 , F01D5/187 , F05D2220/32 , F05D2230/51 , F05D2240/30 , F05D2240/40
摘要： A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.
摘要翻译：燃气轮机系统（120）中的冷却装置。该装置包括多个流动网络单元（208），用于将热量传递到冷却流体;至少一个单元，其包括在第一壁中的开口（64a）之间的第一（218），第二（220）和第三（222）（66）和第二壁（68）中的开口以使冷却流体通过壁。第一部分包括在第一壁的开口和第二部分之间延伸到第二部分的第一流动路径。第三部分包括在第二部分和第二壁中的开口之间的第三流动路径，以实现冷却流体的流动。第二部分包括在第一部分和第三部分之间的一个或多个冷却流体流动路径。第二部分中的流动路径的数量少于第一流动路径的数量，并且少于第三流动路径的数量。

2. 发明授权

US08894363B2 Cooling module design and method for cooling components of a gas turbine system 有权
标题翻译：用于冷却燃气轮机系统组件的冷却模块设计和方法
公开(公告)号：US08894363B2
公开(公告)日：2014-11-25
申请号：US13023716
申请日：2011-02-09
申请人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
发明人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
IPC分类号： F01D5/18
CPC分类号： F01D5/184 , F01D5/186 , F01D5/187 , F05D2220/32 , F05D2230/51 , F05D2240/30 , F05D2240/40
摘要： A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.
摘要翻译：燃气轮机系统（120）中的冷却装置。该装置包括多个流动网络单元（208），用于将热量传递到冷却流体;至少一个单元，包括在第一壁中的开口（64a）之间的第一（218），第二（220）和第三（222）（66）和第二壁（68）中的开口以使冷却流体通过壁。第一部分包括在第一壁的开口和第二部分之间延伸到第二部分的第一流动路径。第三部分包括在第二部分和第二壁中的开口之间的第三流动路径，以实现冷却流体的流动。第二部分包括在第一部分和第三部分之间的一个或多个冷却流体流动路径。第二部分中的流动路径的数量少于第一流动路径的数量，并且少于第三流动路径的数量。

3. 发明授权

US08959886B2 Mesh cooled conduit for conveying combustion gases 有权
标题翻译：用于输送燃烧气体的网状冷却导管
公开(公告)号：US08959886B2
公开(公告)日：2015-02-24
申请号：US12832124
申请日：2010-07-08
申请人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison
发明人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison
IPC分类号： F23R3/06 , F23R3/00 , F01D9/02
CPC分类号： F23R3/005 , F01D9/023 , F23R3/06 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.
摘要翻译：热燃气通过燃气涡轮发动机的导管。导管包括具有内表面，外表面，区域，入口和出口的壁结构。内表面限定导管的内部容积。该区域在内表面和外表面之间延伸并且包括限定多个冷却通道的冷却流体结构。入口从外表面向内延伸，并在入口和通道之间提供流体连通。出口从通道延伸到内表面以在通道和内部容积之间提供流体连通。至少一个第一冷却通道与至少一个第二冷却通道相交，使得流过第一冷却通道的冷却流体与流过第二冷却通道的冷却流体相互作用。

4. 发明申请

US20120006518A1 MESH COOLED CONDUIT FOR CONVEYING COMBUSTION GASES 有权
标题翻译：用于输送燃烧气体的MESH冷却管道
公开(公告)号：US20120006518A1
公开(公告)日：2012-01-12
申请号：US12832124
申请日：2010-07-08
申请人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison
发明人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison
IPC分类号： F28F7/00
CPC分类号： F23R3/005 , F01D9/023 , F23R3/06 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.
摘要翻译：热燃气通过燃气涡轮发动机的导管。导管包括具有内表面，外表面，区域，入口和出口的壁结构。内表面限定导管的内部容积。该区域在内表面和外表面之间延伸并且包括限定多个冷却通道的冷却流体结构。入口从外表面向内延伸，并在入口和通道之间提供流体连通。出口从通道延伸到内表面以在通道和内部容积之间提供流体连通。至少一个第一冷却通道与至少一个第二冷却通道相交，使得流过第一冷却通道的冷却流体与流过第二冷却通道的冷却流体相互作用。

5. 发明授权

US09028207B2 Cooled component wall in a turbine engine 有权
标题翻译：在涡轮发动机中冷却的部件壁
公开(公告)号：US09028207B2
公开(公告)日：2015-05-12
申请号：US12888467
申请日：2010-09-23
申请人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
发明人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

6. 发明授权

US08608443B2 Film cooled component wall in a turbine engine 有权
标题翻译：涡轮发动机中的薄膜冷却部件壁
公开(公告)号：US08608443B2
公开(公告)日：2013-12-17
申请号：US12813602
申请日：2010-06-11
申请人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
发明人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
IPC分类号： F01D9/06 , F01D5/18
CPC分类号： F01D5/186 , F01D5/288 , F01D25/12 , F05D2230/10 , F05D2230/30 , F05D2230/90 , F05D2250/183 , F05D2250/185 , F05D2260/202 , F05D2260/221 , F05D2300/502 , F23R2900/03042 , Y10T29/49236
摘要： A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.
摘要翻译：涡轮发动机中的部件壁。部件壁包括基板，沟槽和多个冷却通道。基板具有与第一表面相对的第一表面和第二表面。沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。第一侧壁包括朝向第二侧壁延伸的多个第一突起。冷却通道从沟槽的第一表面延伸到底表面。冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起中的相应的一个。

7. 发明授权

US09181819B2 Component wall having diffusion sections for cooling in a turbine engine 有权
标题翻译：具有用于在涡轮发动机中冷却的扩散部分的部件壁
公开(公告)号：US09181819B2
公开(公告)日：2015-11-10
申请号：US12813624
申请日：2010-06-11
申请人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
发明人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D25/12 , F01D5/18 , F01D5/186 , Y10T29/4932
摘要： A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.
摘要翻译：形成在涡轮发动机的部件壁上的薄膜冷却结构以及制造薄膜冷却结构的方法。膜冷却结构包括形成在壁中的多个单独的扩散部分，每个扩散部分包括单个冷却通道，用于将冷却空气朝向限定扩散部分的壁的突起引导。膜冷却结构可以由掩模模板形成，该掩模模板包括限定壁中多个待形成的扩散部分的形状的孔。掩模材料可以施加到壁中的掩模模板中的孔中，以便阻挡通过孔露出的冷却通道的出口。可以去除掩模模板并且可以在壁的外表面上施加材料，使得一旦去除了掩模材料，材料就限定了扩散部分。

8. 发明申请

US20120076644A1 COOLED COMPONENT WALL IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机冷却组件墙
公开(公告)号：US20120076644A1
公开(公告)日：2012-03-29
申请号：US12888467
申请日：2010-09-23
申请人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
发明人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F03B11/00 , B21D53/02
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

9. 发明申请

US20110305583A1 COMPONENT WALL HAVING DIFFUSION SECTIONS FOR COOLING IN A TURBINE ENGINE 有权
标题翻译：具有用于在涡轮发动机中冷却的扩散部分的部件壁
公开(公告)号：US20110305583A1
公开(公告)日：2011-12-15
申请号：US12813624
申请日：2010-06-11
申请人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
发明人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： F01D25/12 , F01D5/18 , F01D5/186 , Y10T29/4932
摘要： A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.
摘要翻译：形成在涡轮发动机的部件壁上的薄膜冷却结构以及制造薄膜冷却结构的方法。膜冷却结构包括形成在壁中的多个单独的扩散部分，每个扩散部分包括单个冷却通道，用于将冷却空气朝向限定扩散部分的壁的突起引导。膜冷却结构可以由掩模模板形成，该掩模模板包括限定壁中多个待形成的扩散部分的形状的孔。掩模材料可以施加到壁中的掩模模板中的孔中，以便阻挡通过孔露出的冷却通道的出口。可以去除掩模模板并且可以在壁的外表面上施加材料，使得一旦去除了掩模材料，材料就限定了扩散部分。

10. 发明申请

US20110305582A1 Film Cooled Component Wall in a Turbine Engine 有权
标题翻译：涡轮发动机中的薄膜组件壁
公开(公告)号：US20110305582A1
公开(公告)日：2011-12-15
申请号：US12813602
申请日：2010-06-11
申请人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
发明人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
IPC分类号： F01D5/08 , B23P15/00
CPC分类号： F01D5/186 , F01D5/288 , F01D25/12 , F05D2230/10 , F05D2230/30 , F05D2230/90 , F05D2250/183 , F05D2250/185 , F05D2260/202 , F05D2260/221 , F05D2300/502 , F23R2900/03042 , Y10T29/49236
摘要： A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.
摘要翻译：涡轮发动机中的部件壁。部件壁包括基板，沟槽和多个冷却通道。基板具有与第一表面相对的第一表面和第二表面。沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。第一侧壁包括朝向第二侧壁延伸的多个第一突起。冷却通道从沟槽的第一表面延伸到底表面。冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起中的相应的一个。

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