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1. 发明申请

US20060177310A1 Cooled blade or vane for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片或叶片
公开(公告)号：US20060177310A1
公开(公告)日：2006-08-10
申请号：US11330268
申请日：2006-01-12
申请人： Shailendra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailendra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/211
摘要： A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.
摘要翻译：用于燃气轮机的冷却的叶片或叶片具有从叶片或叶片根部以及叶片或叶片柄开始并具有前缘和后缘以及主叶片或叶片内的主叶片或叶片部分部分，沿径向方向延伸的多个冷却管道以流动方式串联连接，并且第一冷却管道具有沿着前缘流过其中的冷却介质的主流。第二冷却管道具有沿着后缘从叶片或叶片根部流到主叶片或叶片部分的尖端的冷却介质的主流。第一冷却管道的出口经由第一转向区域与布置在第一和第二冷却管道之间的第三冷却管道与第二冷却管道的入口与第二转向区域连通。

2. 发明授权

US07264445B2 Cooled blade or vane for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片或叶片
公开(公告)号：US07264445B2
公开(公告)日：2007-09-04
申请号：US11330268
申请日：2006-01-12
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/211
摘要： A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.
摘要翻译：用于燃气轮机的冷却的叶片或叶片具有从叶片或叶片根部以及叶片或叶片柄开始并具有前缘和后缘以及主叶片或叶片内的主叶片或叶片部分部分，沿径向方向延伸的多个冷却管道以流动方式串联连接，并且第一冷却管道具有沿着前缘流过其中的冷却介质的主流。第二冷却管道具有沿着后缘从叶片或叶片根部流到主叶片或叶片部分的尖端的冷却介质的主流。第一冷却管道的出口经由第一转向区域与布置在第一和第二冷却管道之间的第三冷却管道与第二冷却管道的入口与第二转向区域连通。

3. 发明申请

US20060292006A1 Cooled blade for a gas turbine 有权
公开(公告)号：US20060292006A1
公开(公告)日：2006-12-28
申请号：US11483091
申请日：2006-07-10
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/50 , F05D2260/205 , F05D2260/221
摘要： A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.

4. 发明授权

US07520724B2 Cooled blade for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片
公开(公告)号：US07520724B2
公开(公告)日：2009-04-21
申请号：US11483091
申请日：2006-07-10
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/50 , F05D2260/205 , F05D2260/221
摘要： A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.
摘要翻译：用于燃气涡轮机的冷却叶片具有叶片翼型件，叶片翼型件从叶片根部和叶片柄部突出并且具有前缘和后缘，并且在叶片翼型件内，在流动方面，多个顺序的冷却剂管道，沿径向延伸。沿着前缘的第一冷却剂管道和沿着后缘的第二冷却剂管道具有从叶片根部到叶片翼型的尖端流过它们的冷却剂的主流。第一冷却剂管道的入口与主冷却剂入口连接，并且第一冷却剂管道的出口经由第一偏转区域与第二冷却剂管道的入口连接。第三冷却剂管道布置在第一和第二冷却剂管道和第二偏转区域之间。从外部提供的另外冷却剂冷却流从第三冷却剂管道加入流入第二冷却剂管道的冷却剂的加热主流。孔可以例如从主冷却剂入口延伸到第二偏转区域。

5. 发明授权

US09435213B2 Method for improving the sealing on rotor arrangements 有权
标题翻译：改善转子装置密封的方法
公开(公告)号：US09435213B2
公开(公告)日：2016-09-06
申请号：US12701852
申请日：2010-02-08
申请人： Helmar Wunderle , Stefan Schlechtriem , Peter Graf , Silvio Glaser , Beat Von Arx
发明人： Helmar Wunderle , Stefan Schlechtriem , Peter Graf , Silvio Glaser , Beat Von Arx
IPC分类号： F01D5/30 , F01D11/00
CPC分类号： F01D5/3007 , F01D11/005 , F05D2240/55 , F05D2250/13 , F05D2250/182 , Y10T29/49316
摘要： A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described.
摘要翻译：描述了一种用于改善转子和多个叶片之间的密封的方法。转子具有多个大致轴向延伸的成型凹槽，具有对应的叶片根部轮廓的叶片环以大致轴向的插入方向以形状配合和/或摩擦锁定的方式插入到该凹槽中。在凹部之间，转子具有在轴向和圆周方向上延伸的切向表面部分或圆周表面部分，并且在径向方向上通常间接地被周向相邻布置的叶片的下部护罩覆盖。切向表面或周向表面部分中的至少一个在径向方向上设置有台阶，并且在其上方布置有叶片的护罩的下侧设置相应的凹陷，该凹槽邻近齐平。还描述了相应的转子或叶片。

6. 发明授权

US08632309B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US08632309B2
公开(公告)日：2014-01-21
申请号：US13091605
申请日：2011-04-21
申请人： Igor Tsypkaykin , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
发明人： Igor Tsypkaykin , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译：公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。每个侧轨分为不同高度和/或宽度的部分。

7. 发明申请

US20110286849A1 BLADE FOR A GAS TURBINE 有权
标题翻译：燃气轮机叶片
公开(公告)号：US20110286849A1
公开(公告)日：2011-11-24
申请号：US13091605
申请日：2011-04-21
申请人： Igor TSYPKAYKIN , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
发明人： Igor TSYPKAYKIN , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译：公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。每个侧轨分为不同高度和/或宽度的部分。

8. 发明申请

US20110189002A1 TURBINE GUIDE VANE 审中-公开
标题翻译：涡轮导向槽
公开(公告)号：US20110189002A1
公开(公告)日：2011-08-04
申请号：US13012317
申请日：2011-01-24
申请人： Georgeta-Ileana Panaite , Igor Tsypkaykin , Beat Von Arx , Andre Saxer
发明人： Georgeta-Ileana Panaite , Igor Tsypkaykin , Beat Von Arx , Andre Saxer
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/64 , F05D2240/80
摘要： A turbine guide vane (10) has a platform (12) from which at least a guide vane blade (13) extends. The platform (12) has a front rail (18) and a rear rail (20) arranged to be housed in guide vane carrier seats (19, 21). The front and rear rails (18, 20) have projecting pads (23, 24) arranged to rest against the guide vane carrier seats (19, 21). The front and rear rails (18, 20) have at least two pads (23) extending from one side of the front and rear rails (18, 20) and at least two further pads (24) extending from an opposite side of the front and rear rails (18, 20). The pads (23, 24) extend from opposite circumferential portions (26) of the front and rear rails (18, 20). The pads (23, 24) extending from the same circumferential portion (26) of the front and rear rails (18, 20) are at least partly staggered with respect to one another.
摘要翻译：涡轮引导叶片（10）具有平台（12），至少一个导叶叶片（13）从该平台延伸。平台（12）具有布置成容纳在导向叶片承载座（19,21）中的前轨（18）和后轨（20）。前导轨和后导轨（18,20）具有布置成抵靠引导叶片承载座（19,21）的突出垫（23,24）。前导轨和后导轨（18,20）具有从前后导轨（18,20）的一侧延伸的至少两个焊盘（23）和从前部的相对侧延伸的至少两个另外的焊盘（24）和后导轨（18,20）。垫（23,24）从前后导轨（18,20）的相对周向部分（26）延伸。从前后导轨（18,20）的同一圆周部分（26）延伸的焊盘（23,24）相对于彼此至少部分地交错。

9. 发明授权

US06547525B2 Cooled component, casting core for manufacturing such a component, as well as method for manufacturing such a component 有权
公开(公告)号：US06547525B2
公开(公告)日：2003-04-15
申请号：US09984204
申请日：2001-10-29
申请人： Hartmut Haehnle , Ibrahim El-Nashar , Rudolf Kellerer , Beat Von Arx
发明人： Hartmut Haehnle , Ibrahim El-Nashar , Rudolf Kellerer , Beat Von Arx
IPC分类号： F01D508
CPC分类号： F01D5/187 , B22C9/10 , B22C9/24 , Y10T29/49341
摘要： A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.

10. 发明授权

US06516865B1 Hollow-cast component 有权
标题翻译：空心铸件
公开(公告)号：US06516865B1
公开(公告)日：2003-02-11
申请号：US09650407
申请日：2000-08-29
申请人： Alexander Beeck , Erhard Kreis , Ibrahim El-Nashar , Beat Von Arx
发明人： Alexander Beeck , Erhard Kreis , Ibrahim El-Nashar , Beat Von Arx
IPC分类号： B22D2704
CPC分类号： B22C21/14 , B22D31/002 , Y10S415/915 , Y10T29/49742 , Y10T29/49744
摘要： In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.
摘要翻译：在中空铸造部件中，在制造期间产生的芯开口（13）用封闭件（14）封闭。该封闭件位于部件中的凹部（15）的内部，由此将凹部布置成完全嵌入铸造材料中，并且完全覆盖芯部开口。由于这种安装，封闭件在两个空间轴的方向上以形状配合的方式固定，使得封闭件仅需要在安装方向上用附加的接头固定。优选的是，安装方向相对于封闭件的最大应力的方向是正常的，使得接头承受相对较小的应力，因此可以以少量的支出和高度的操作安全性来制造。

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