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1. 发明授权

US07097425B2 Microcircuit cooling for a turbine airfoil 有权
标题翻译：用于涡轮机翼的微电路冷却
公开(公告)号：US07097425B2
公开(公告)日：2006-08-29
申请号：US10802260
申请日：2004-03-16
申请人： Frank J. Cunha , Keith Santeler , Scott W. Gayman , Eric Couch
发明人： Frank J. Cunha , Keith Santeler , Scott W. Gayman , Eric Couch
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/25 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.
摘要翻译：涡轮机翼片包括嵌入压力和抽吸侧壁内的多个冷却回路以及第一和第二流动通道。第一流动通道将冷却剂流体供给到仅在压力侧壁内嵌入的冷却回路，而第二流动通道将冷却剂流体供给到仅嵌入在吸力侧壁内的冷却回路。本发明的方法实施例包括将嵌入在第一侧壁内的冷却回路的入口放置成仅与流动通道中的一个流体连通，并且将嵌入在第二侧壁内的冷却回路的入口与至少一个其他流动通道以最小化吸入和压力侧壁的吸收压力的差异，以确保将冷却剂流体摄入相应冷却回路的入口。

2. 发明授权

US07255536B2 Turbine airfoil platform cooling circuit 有权
标题翻译：涡轮机翼平台冷却回路
公开(公告)号：US07255536B2
公开(公告)日：2007-08-14
申请号：US11134927
申请日：2005-05-23
申请人： Frank J. Cunha , Eric Couch , Keith A. Santeler , Scott W. Gayman , Eric A. Hudson , Christopher Joe , Eric Letizia
发明人： Frank J. Cunha , Eric Couch , Keith A. Santeler , Scott W. Gayman , Eric A. Hudson , Christopher Joe , Eric Letizia
IPC分类号： F01D5/18
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.
摘要翻译：机翼组件包括远离平台延伸的翼型件。通过平台形成一个或多个冷却回路以提供平台的冷却。冷却回路可以包括从平台下方接收冷却空气的向下定向的入口。然后将冷却空气沿大致平行于平台的外表面的方向引导并通过平台的外表面形成的出口。冷却回路可以可选地包括从冷却回路的外壁延伸到内壁的多个基座，以增加冷却回路的刚度和冷却功能。

3. 发明授权

US08742279B2 Method of creating an airfoil trench and a plurality of cooling holes within the trench 有权
标题翻译：在槽内形成翼型槽和多个冷却孔的方法
公开(公告)号：US08742279B2
公开(公告)日：2014-06-03
申请号：US12697437
申请日：2010-02-01
申请人： Jesse Gannelli , Scott W. Gayman , Edward F. Pietraszkiewicz , Christopher B. Jelks , Sandra S. Pinero , Paul Thomas Rembish , Ryan Shepard Levy
发明人： Jesse Gannelli , Scott W. Gayman , Edward F. Pietraszkiewicz , Christopher B. Jelks , Sandra S. Pinero , Paul Thomas Rembish , Ryan Shepard Levy
IPC分类号： B23K9/00
CPC分类号： B23H1/04 , B23H9/10 , B23H9/14
摘要： A tool for forming a trench and a plurality of cooling holes within the trench includes a body, the body including a ridge portion extending along a first side of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.
摘要翻译：用于在槽内形成沟槽和多个冷却孔的工具包括主体，主体包括沿着工具的第一侧延伸的脊部。脊部可操作以与工件配合以在工件上形成沟槽。多个电极从脊部延伸并且被定向成在工件上的沟槽内形成多个冷却孔。

4. 发明申请

US20080138209A1 High aspect ratio blade main core modifications for peripheral serpentine microcircuits 有权
标题翻译：外围蛇形微电路的高纵横比刀片主芯修改
公开(公告)号：US20080138209A1
公开(公告)日：2008-06-12
申请号：US11636801
申请日：2006-12-11
申请人： Francisco J. Cunha , Scott W. Gayman
发明人： Francisco J. Cunha , Scott W. Gayman
IPC分类号： F01D5/18
CPC分类号： B22C9/103 , B22C9/04 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/202 , Y02T50/676
摘要： A turbine engine component, such as a turbine blade, has an airfoil portion having a pressure side wall and a suction side wall, a first cooling circuit embedded within the pressure side wall, which first cooling circuit has at least two passageways embedded within the pressure side wall, a second cooling circuit embedded within the suction side wall, which second cooling circuit has at least two passageways embedded within the suction side wall, at least one cooling fluid supply cavity located between the pressure and suction side walls, each cooling fluid supply cavity having at least one projecting portion extending between adjacent ones of the embedded passageways in the first cooling circuit or adjacent ones of the embedded passageways in the second cooling circuit, and each projecting portion communicating with at least one film cooling hole. A method for forming the turbine blade component is also described.
摘要翻译：诸如涡轮叶片的涡轮发动机部件具有翼型部分，其具有压力侧壁和吸力侧壁，嵌入在压力侧壁内的第一冷却回路，该第一冷却回路具有嵌入在压力内的至少两个通道侧壁，嵌入在吸入侧壁内的第二冷却回路，该第二冷却回路具有嵌入吸入侧壁内的至少两个通道，位于压力侧和吸力侧壁之间的至少一个冷却流体供应腔，每个冷却流体供应空腔具有在第一冷却回路中相邻的嵌入通道之间延伸的至少一个突出部分或第二冷却回路中相邻的嵌入通道中的一个突出部分，并且每个突出部分与至少一个膜冷却孔连通。还描述了用于形成涡轮叶片部件的方法。

5. 发明申请

US20110186550A1 METHOD OF CREATING AN AIRFOIL TRENCH AND A PLURALITY OF COOLING HOLES WITHIN THE TRENCH 有权
标题翻译：在TRENCH中制造空气涡轮的方法和多个冷却孔
公开(公告)号：US20110186550A1
公开(公告)日：2011-08-04
申请号：US12697437
申请日：2010-02-01
申请人： Jesse Gannelli , Scott W. Gayman , Edward F. Pietraszkiewicz , Christopher B. Jelks , Sandra S. Pinero , Paul Thomas Rembish , Ryan Shepard Levy
发明人： Jesse Gannelli , Scott W. Gayman , Edward F. Pietraszkiewicz , Christopher B. Jelks , Sandra S. Pinero , Paul Thomas Rembish , Ryan Shepard Levy
IPC分类号： B23K9/013
CPC分类号： B23H1/04 , B23H9/10 , B23H9/14
摘要： A tool for forming a trench and a plurality of cooling holes within the trench includes a body, the body including a ridge portion extending along a first side of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.
摘要翻译：用于在槽内形成沟槽和多个冷却孔的工具包括主体，主体包括沿着工具的第一侧延伸的脊部。脊部可操作以与工件配合以在工件上形成沟槽。多个电极从脊部延伸并且被定向成在工件上的沟槽内形成多个冷却孔。

6. 发明授权

US07717676B2 High aspect ratio blade main core modifications for peripheral serpentine microcircuits 有权
标题翻译：外围蛇形微电路的高纵横比刀片主芯修改
公开(公告)号：US07717676B2
公开(公告)日：2010-05-18
申请号：US11636801
申请日：2006-12-11
申请人： Francisco J. Cunha , Scott W. Gayman
发明人： Francisco J. Cunha , Scott W. Gayman
IPC分类号： F01D5/18
CPC分类号： B22C9/103 , B22C9/04 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/202 , Y02T50/676
摘要： A turbine engine component, such as a turbine blade, has an airfoil portion having a pressure side wall and a suction side wall, a first cooling circuit embedded within the pressure side wall, which first cooling circuit has at least two passageways embedded within the pressure side wall, a second cooling circuit embedded within the suction side wall, which second cooling circuit has at least two passageways embedded within the suction side wall, at least one cooling fluid supply cavity located between the pressure and suction side walls, each cooling fluid supply cavity having at least one projecting portion extending between adjacent ones of the embedded passageways in the first cooling circuit or adjacent ones of the embedded passageways in the second cooling circuit, and each projecting portion communicating with at least one film cooling hole. A method for forming the turbine blade component is also described.
摘要翻译：诸如涡轮叶片的涡轮发动机部件具有翼型部分，其具有压力侧壁和吸力侧壁，嵌入在压力侧壁内的第一冷却回路，该第一冷却回路具有嵌入在压力内的至少两个通道侧壁，嵌入在吸入侧壁内的第二冷却回路，该第二冷却回路具有嵌入吸入侧壁内的至少两个通道，位于压力侧和吸力侧壁之间的至少一个冷却流体供应腔，每个冷却流体供应空腔具有在第一冷却回路中相邻的嵌入通道之间延伸的至少一个突出部分或第二冷却回路中相邻的嵌入通道中的一个突出部分，并且每个突出部分与至少一个膜冷却孔连通。还描述了用于形成涡轮叶片部件的方法。

7. 发明授权

US07980820B2 Turbine engine blade cooling 有权
标题翻译：涡轮发动机叶片冷却
公开(公告)号：US07980820B2
公开(公告)日：2011-07-19
申请号：US11845418
申请日：2007-08-27
申请人： Scott W. Gayman , Justin D. Piggush , Edward F. Pietraszkiewicz , William A. Agli, III
发明人： Scott W. Gayman , Justin D. Piggush , Edward F. Pietraszkiewicz , William A. Agli, III
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2300/611 , Y10T29/49336
摘要： A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.
摘要翻译：为包括外表面的涡轮发动机提供叶片。外表面包括具有热障涂层的部分和与热障涂层相邻的未涂覆的搁板，而没有热障涂层。冷却孔从内部通道穿过外表面延伸到出口。裂缝通道凹进外表面并与出口处的冷却孔相互连接。被切割的通道延伸到叶片尖端端面。围绕通道保护从冷却孔排出的冷却流体与包围叶片的二次流，否则将与冷却流体混合并分散冷却流体。裂缝通道还增加暴露于冷却流体的表面积以增加传热速率。

8. 发明申请

US20090060741A1 TURBINE ENGINE BLADE COOLING 有权
标题翻译：涡轮发动机叶片冷却
公开(公告)号：US20090060741A1
公开(公告)日：2009-03-05
申请号：US11845418
申请日：2007-08-27
申请人： Scott W. Gayman , Justin D. Piggush , Edward F. Pietraszkiewicz , William A. Agli, III
发明人： Scott W. Gayman , Justin D. Piggush , Edward F. Pietraszkiewicz , William A. Agli, III
IPC分类号： F04D29/58 , B21D53/78 , F01D5/18
CPC分类号： F01D5/20 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2300/611 , Y10T29/49336
摘要： A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.
摘要翻译：为包括外表面的涡轮发动机提供叶片。外表面包括具有热障涂层的部分和与热障涂层相邻的未涂覆的搁板，而没有热障涂层。冷却孔从内部通道穿过外表面延伸到出口。裂缝通道凹进外表面并与出口处的冷却孔相互连接。被切割的通道延伸到叶片尖端端面。围绕通道保护从冷却孔排出的冷却流体与包围叶片的二次流，否则将与冷却流体混合并分散冷却流体。裂缝通道还增加暴露于冷却流体的表面积以增加传热速率。

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