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1. 发明授权

EP1820937B1 TURBINE BLADE WITH RADIAL COOLING CHANNELS 有权转让
公开(公告)号：EP1820937B1
公开(公告)日：2020-01-08
申请号：EP07250527.4
申请日：2007-02-09
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Sharma, Om P. , Chin, Kar D.
IPC分类号： F01D5/18 , F01D25/12

2. 发明授权

EP2540430B1 Electric discharge machining hole drilling 有权转让
标题翻译：放电加工孔钻孔
公开(公告)号：EP2540430B1
公开(公告)日：2017-12-13
申请号：EP12174236.5
申请日：2012-06-28
申请人： United Technologies Corporation
发明人： Mironets, Sergey , Koonankeil, James M. , Pietraszkiewicz, Edward F. , Davis, Thomas R.
IPC分类号： B23H1/02 , B23H9/10 , B23H9/14
CPC分类号： B23H9/10 , B23H1/02 , B23H9/14
摘要： An apparatus and method for machining apertures into a conductive workpiece (10) is disclosed. The apparatus has a tank (34) capable of holding a dielectric fluid, and a fixture (24) for holding the workpiece in the tank. An electric discharge machine with an electrode (36), a power supply connected to the electrode that produces machining pulses for electric discharge machining through the workpiece, and a controller (39) for regulating the power supply and electrode position is also part of the apparatus. Finally, the apparatus has a pressure transducer (33) connected to the fixture, and a process controller (38) in communication with the electric discharge machine controller and pressure transducer.

3. 发明公开

EP2557271A3 Method of measuring turbine blade tip erosion 有权转让
标题翻译：测量所述涡轮机转子尖端侵蚀的方法
公开(公告)号：EP2557271A3
公开(公告)日：2016-12-07
申请号：EP12179735.1
申请日：2012-08-08
申请人： United Technologies Corporation
发明人： Funk, Stanley J. , Pietraszkiewicz, Edward F.
IPC分类号： F01D5/20
CPC分类号： F01D21/003 , F01D5/141 , F01D5/20 , F01D25/24 , F05D2220/32 , F05D2230/50 , F05D2240/307 , F05D2260/83 , Y10T29/49336
摘要： A method of designing a turbine blade (32) includes the steps of forming at least two notches (60) on a tip of a turbine blade (32), each of the at least two notches (60) having a known dimension. The turbine blade (32) has a pressure side (56) and a suction side (58). The method further includes the step of operating a gas turbine engine including the turbine blade (32) to expand a length of the turbine blade (32) such that the tip (42) of the turbine blade (32) engages a casing (36). The method further includes the steps of viewing the tip (42) of the turbine blade (32) after the step of operating of the gas turbine engine, determining an appearance of the notches (60) on the tip (42) and determining a manufacturing length of the turbine blade (32) based on the step of determining the appearance the notches (60).

4. 发明授权

EP2628903B1 Gas Turbine Engine Airfoil Cooling Circuit 有权转让
标题翻译：燃气涡轮发动机的翼型件冷却回路
公开(公告)号：EP2628903B1
公开(公告)日：2015-03-18
申请号：EP12197302.8
申请日：2012-12-14
申请人： United Technologies Corporation
发明人： Propheter-Hinckley, Tracy A. , Perez, Rafael A. , Pietraszkiewicz, Edward F.
IPC分类号： F01D9/04 , F01D5/18
CPC分类号： F01D5/186 , F01D9/041 , F05D2240/12 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676

5. 发明公开

EP2628903A3 Gas Turbine Engine Airfoil Cooling Circuit 有权转让
标题翻译：燃气涡轮发动机翼型冷却回路
公开(公告)号：EP2628903A3
公开(公告)日：2013-11-13
申请号：EP12197302.8
申请日：2012-12-14
申请人： United Technologies Corporation
发明人： Propheter-Hinckley, Tracy A. , Perez, Rafael A. , Pietraszkiewicz, Edward F.
IPC分类号： F01D9/04 , F01D5/18
CPC分类号： F01D5/186 , F01D9/041 , F05D2240/12 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil (40) for a gas turbine engine includes an airfoil body (42) and a cooling circuit (70) defined within the airfoil body (42). The cooling circuit (70) includes at least a first cavity (74) in fluid communication with a second cavity (76). A first portion (84) of the first cavity (74) extends between an outer diameter and an inner diameter of the airfoil body (42) and a second portion (86) of the first cavity (74) extends across a space (89) between a leading edge (48) and a trailing edge (50) of the airfoil body (42).
摘要翻译：用于燃气涡轮发动机的翼型件（40）包括翼型体（42）和限定在翼型体（42）内的冷却回路（70）。冷却回路（70）至少包括与第二空腔（76）流体连通的第一空腔（74）。第一腔体（74）的第一部分（84）在翼型体（42）的外径和内径之间延伸，并且第一腔体（74）的第二部分（86）延伸穿过空间（89）在翼型体（42）的前缘（48）和后缘（50）之间。

6. 发明公开

EP2610438A2 Airflow testing method and system for multiple cavity blades and vanes 有权转让
标题翻译： Luftstromprüfverfahrenund SystemfürSchaufeln mit mehrerenAuswölbungen
公开(公告)号：EP2610438A2
公开(公告)日：2013-07-03
申请号：EP12198196.3
申请日：2012-12-19
申请人： United Technologies Corporation
发明人： Mironets, Sergey , Davis, Thomas R. , Varsell, Richard , Pietraszkiewicz, Edward F.
IPC分类号： F01D21/00 , F01D5/18
CPC分类号： F01D21/003 , F01D5/18
摘要： A system for airflow testing a turbine engine component (12) having multiple cavities (22, 24, 26) has a test fixture (10) with a module for supporting a turbine engine component (12) to be tested and a sliding element (46) for sequentially allowing a pressurized fluid to flow through each of the multiple cavities (22, 24, 26) in the turbine engine component (12). A method for performing the airflow testing is also described.
摘要翻译：一种用于气流测试的具有多个空腔（22,24,26）的涡轮发动机部件（12）的系统具有测试夹具（10），其具有用于支撑待测试的涡轮发动机部件（12）的模块和滑动元件（46 ），用于顺序地允许加压流体流过涡轮发动机部件（12）中的多个空腔（22,24,26）中的每一个。还描述了用于执行气流测试的方法。

7. 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.

8. 发明公开

EP2022941A3 Turbine blade of a gas turbine engine and corresponding method of cooling this blade 有权转让
标题翻译：燃气涡轮发动机的涡轮机叶片和用于冷却该涡轮机叶片的方法对应
公开(公告)号：EP2022941A3
公开(公告)日：2011-01-05
申请号：EP08252498.4
申请日：2008-07-23
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Kohli, Atul
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2230/21 , F05D2250/185 , F05D2260/202
摘要： A blade for a turbine engine includes structure providing spaced apart suction and pressure sides (40,42). A cooling passage (44) includes a first passageway (48) near the pressure side (42) and a second passageway (52,56) in fluid communication with the first passageway (48). The second passageway (52,56) is arranged between the first passageway (48) and the suction side (40). The cooling passage (44) provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges (36,38) of the blade. During use, cooling fluid is supplied to the pressure side (42) through first cooling apertures (60) fluidly connected to the first passageway (48) and to the suction side (40) through second cooling apertures (62) fluidly connected to the other passage way (52,56). The first passageway (48) is at a higher pressure that then second passageway (52,56) so that cooling fluid is provided by the cooling passage (44) to the pressure and suction sides (40,42) in a balanced fashion.

9. 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。

10. 发明公开

EP2022941A2 Turbine blade of a gas turbine engine and corresponding method of cooling this blade 有权转让
标题翻译： Turbinenschaufel von einem Gasturbinentriebwerk
公开(公告)号：EP2022941A2
公开(公告)日：2009-02-11
申请号：EP08252498.4
申请日：2008-07-23
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Kohli, Atul
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2230/21 , F05D2250/185 , F05D2260/202
摘要： A blade for a turbine engine includes structure providing spaced apart suction and pressure sides (40,42). A cooling passage (44) includes a first passageway (48) near the pressure side (42) and a second passageway (52,56) in fluid communication with the first passageway (48). The second passageway (52,56) is arranged between the first passageway (48) and the suction side (40). The cooling passage (44) provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges (36,38) of the blade. During use, cooling fluid is supplied to the pressure side (42) through first cooling apertures (60) fluidly connected to the first passageway (48) and to the suction side (40) through second cooling apertures (62) fluidly connected to the other passage way (52,56). The first passageway (48) is at a higher pressure that then second passageway (52,56) so that cooling fluid is provided by the cooling passage (44) to the pressure and suction sides (40,42) in a balanced fashion.
摘要翻译：用于涡轮发动机的叶片包括提供间隔开的吸力和压力侧面（40,42）的结构。冷却通道（44）包括靠近压力侧（42）的第一通道（48）和与第一通道（48）流体连通的第二通道（52,56）。第二通道（52,56）布置在第一通道（48）和吸力侧（40）之间。冷却通道（44）提供蛇形冷却路径，其沿横向于在叶片的后缘和前缘（36,38）之间延伸的弦线的方向布置。在使用期间，冷却流体通过流体地连接到第一通道（48）的第一冷却孔（60）和通过流体连接到另一个的第二冷却孔（62）而被吸入侧（40）供应到压力侧通行方式（52,56）。第一通道（48）处于比第二通道（52,56）更高的压力，使得冷却流体以平衡的方式由冷却通道（44）提供给压力侧和吸力侧（40,42）。

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