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1. 发明授权

EP2031186B1 Turbine engine blade cooling 有权转让
标题翻译：冷却系统的燃气涡轮机叶片
公开(公告)号：EP2031186B1
公开(公告)日：2015-10-14
申请号：EP08252810.0
申请日：2008-08-22
申请人： United Technologies Corporation
发明人： Gayman, Scott W. , Piggush, Justin D. , Pietraszkiewicz, Edward F. , Agli, William A., III
IPC分类号： F01D5/18 , F01D5/20 , F01D5/28
CPC分类号： F01D5/20 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2300/611 , Y10T29/49336

2. 发明公开

EP2031186A3 Turbine engine blade cooling 有权转让
标题翻译：冷却系统的燃气涡轮机叶片
公开(公告)号：EP2031186A3
公开(公告)日：2011-11-09
申请号：EP08252810.0
申请日：2008-08-22
申请人： United Technologies Corporation
发明人： Gayman, Scott W. , Piggush, Justin D. , Pietraszkiewicz, Edward F. , Agli, William A., III
IPC分类号： F01D5/18 , F01D5/20 , F01D5/28
CPC分类号： F01D5/20 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2300/611 , Y10T29/49336
摘要： A blade (20) for a turbine engine includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating (52) and an uncoated shelf (56) adjacent to the thermal barrier coating (52) without the thermal barrier coating (52). A cooling hole (48) extends from an internal passageway through the exterior surface to an exit (54). A scarfed channel (62) is recessed in the exterior surface and interconnected to the cooling hole (48) at the exit (54). The scarfed channel (62) extends to a blade tip end surface (68). The scarfed channel (62) protects the cooling fluid exiting the cooling hole (48) from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels (62) also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.

3. 发明公开

EP2031186A2 Turbine engine blade cooling 有权转让
标题翻译： Kühlsystemfüreine Gasturbinenschaufel
公开(公告)号：EP2031186A2
公开(公告)日：2009-03-04
申请号：EP08252810.0
申请日：2008-08-22
申请人： United Technologies Corporation
发明人： Gayman, Scott W. , Piggush, Justin D. , Pietraszkiewicz, Edward F. , Agli, William A., 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 (20) for a turbine engine includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating (52) and an uncoated shelf (56) adjacent to the thermal barrier coating (52) without the thermal barrier coating (52). A cooling hole (48) extends from an internal passageway through the exterior surface to an exit (54). A scarfed channel (62) is recessed in the exterior surface and interconnected to the cooling hole (48) at the exit (54). The scarfed channel (62) extends to a blade tip end surface (68). The scarfed channel (62) protects the cooling fluid exiting the cooling hole (48) from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels (62) also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.
摘要翻译：用于涡轮发动机的叶片（20）包括外表面。外表面包括具有隔热涂层（52）的部分和与热障涂层（52）相邻的未涂覆的搁板（56），而没有隔热涂层（52）。冷却孔（48）从内部通道穿过外表面延伸到出口（54）。在外表面上凹陷的通道（62）并且在出口（54）处与冷却孔48相互连接。被切割的通道（62）延伸到叶片尖端端面（68）。裂缝通道（62）保护离开冷却孔（48）的冷却流体免受围绕叶片的二次流动，否则将与冷却流体混合并分散冷却流体。裂缝通道（62）还增加暴露于冷却流体的表面积，以增加传热速率。

4. 发明公开

EP1726785A3 Turbine airfoil platform cooling circuit 有权转让
标题翻译：一个涡轮叶片的平台的冷却通道
公开(公告)号：EP1726785A3
公开(公告)日：2009-12-30
申请号：EP06251550.7
申请日：2006-03-23
申请人： United Technologies Corporation
发明人： Cunha, Frank J. , Couch, Eric , Santeler, Keith A. , Letizia, Eric , Gayman, Scott W. , Hudson, Eric A. , Joe, Christopher
IPC分类号： F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil assembly (20) includes an airfoil (34) extending away from a platform (32). One or more cooling circuits (42, 46) are formed through the platform (32) in order to provide cooling of the platform (32). The cooling circuit (42, 46) may include a downwardly directed inlet (44, 50) receiving cooling air from below the platform (32). The cooling air is then directed in a direction generally parallel to the outer surface of the platform (32) and through exits (38, 54) formed through the outer surface of the platform (32). The cooling circuit (42, 46) may optionally include a plurality of pedestals (56) 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.

5. 发明公开

EP1726785A2 Turbine airfoil platform cooling circuit 有权转让
标题翻译： Kühlkanalder Plattform einer Turbinenschaufel
公开(公告)号：EP1726785A2
公开(公告)日：2006-11-29
申请号：EP06251550.7
申请日：2006-03-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Cunha, Frank J. , Couch, Eric , Santeler, Keith A. , Letizia, Eric , Gayman, Scott W. , Hudson, Eric A. , Joe, Christopher
IPC分类号： F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil assembly (20) includes an airfoil (34) extending away from a platform (32). One or more cooling circuits (42, 46) are formed through the platform (32) in order to provide cooling of the platform (32). The cooling circuit (42, 46) may include a downwardly directed inlet (44, 50) receiving cooling air from below the platform (32). The cooling air is then directed in a direction generally parallel to the outer surface of the platform (32) and through exits (38, 54) formed through the outer surface of the platform (32). The cooling circuit (42, 46) may optionally include a plurality of pedestals (56) 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（20）包括从平台（32）延伸的翼型件（34）。通过平台（32）形成一个或多个冷却回路（42,46），以提供平台（32）的冷却。冷却回路（42,46）可以包括从平台（32）下方接收冷却空气的向下定向的入口（44,50）。然后，冷却空气沿着大致平行于平台（32）的外表面的方向并通过穿过平台（32）的外表面形成的出口（38,54）引导。冷却回路（42,46）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（56），以增加冷却回路的刚度和冷却功能。

6. 发明授权

EP2359972B1 Method of creating an airfoil trench and a plurality of cooling holes within the trench 有权转让
标题翻译：在沟槽内形成翼型沟槽和多个冷却孔的方法
公开(公告)号：EP2359972B1
公开(公告)日：2018-01-24
申请号：EP11250110.1
申请日：2011-02-01
申请人： United Technologies Corporation
发明人： Gannelli, Jesse , Pinero, Sandra S. , Rembish, Paul Thomas , Levy, Ryan Shepard , Gayman, Scott W. , Pietraszkiewicz, Edward F. , Jelks, Christopher B.
IPC分类号： B23H1/04 , B23H9/10 , B23H9/14
CPC分类号： B23H1/04 , B23H9/10 , B23H9/14
摘要： A tool (30) for forming a trench and a plurality of cooling holes within the trench includes a body (31), the body including a ridge portion (32) extending along a first side (33) of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes (34) extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.

7. 发明授权

EP1577498B1 Microcircuit cooling for a turbine airfoil 有权
标题翻译：微型电路冷却涡轮机翼型
公开(公告)号：EP1577498B1
公开(公告)日：2007-01-17
申请号：EP05251603.6
申请日：2005-03-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Cunha, Frank J. , Santeler, Keith , Gayman, Scott W. , Couch, Eric
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/25 , F05D2260/2212 , F05D2260/22141 , Y02T50/676

8. 发明公开

EP2359972A3 Method of creating an airfoil trench and a plurality of cooling holes within the trench 有权转让
标题翻译：一种用于在槽制备翼槽和多个冷却孔的过程
公开(公告)号：EP2359972A3
公开(公告)日：2012-05-02
申请号：EP11250110.1
申请日：2011-02-01
申请人： United Technologies Corporation
发明人： Gannelli, Jesse , Pinero, Sandra S. , Rembish, Paul Thomas , Levy, Ryan Shepard , Gayman, Scott W. , Pietraszkiewicz, Edward F. , Jelks, Christopher B.
IPC分类号： B23H1/04 , B23H9/10 , B23H9/14
CPC分类号： B23H1/04 , B23H9/10 , B23H9/14
摘要： A tool (30) for forming a trench and a plurality of cooling holes within the trench includes a body (31), the body including a ridge portion (32) extending along a first side (33) of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes (34) extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.

9. 发明公开

EP2359972A2 Method of creating an airfoil trench and a plurality of cooling holes within the trench 有权转让
标题翻译： Verfahren zur Herstellung einerTragflächenchecheund mehrereKühlöffnungenin der Furche
公开(公告)号：EP2359972A2
公开(公告)日：2011-08-24
申请号：EP11250110.1
申请日：2011-02-01
申请人： United Technologies Corporation
发明人： Gannelli, Jesse , Pinero, Sandra S. , Rembish, Paul Thomas , Levy, Ryan Shepard , Gayman, Scott W. , Pietraszkiewicz, Edward F. , Jelks, Christopher B.
IPC分类号： B23H1/04 , B23H9/10 , B23H9/14
CPC分类号： B23H1/04 , B23H9/10 , B23H9/14
摘要： A tool (30) for forming a trench and a plurality of cooling holes within the trench includes a body (31), the body including a ridge portion (32) extending along a first side (33) of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes (34) 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：用于在沟槽内形成沟槽和多个冷却孔的工具（30）包括主体（31），主体包括沿工具的第一侧（33）延伸的脊部（32）。脊部可操作以与工件配合以在工件上形成沟槽。多个电极（34）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。

10. 发明授权

EP1726785B1 Turbine airfoil platform cooling circuit 有权转让
标题翻译：一个涡轮叶片的平台的冷却通道
公开(公告)号：EP1726785B1
公开(公告)日：2011-07-20
申请号：EP06251550.7
申请日：2006-03-23
申请人： United Technologies Corporation
发明人： Cunha, Frank J. , Couch, Eric , Santeler, Keith A. , Letizia, Eric , Gayman, Scott W. , Hudson, Eric A. , Joe, Christopher
IPC分类号： F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676

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