公开(公告)号：US08382433B2

公开(公告)日：2013-02-26

申请号：US13113630

申请日：2011-05-23

Applicant: Brian Kenneth Wardle ,  Beat Von Arx

Inventor： Brian Kenneth Wardle ,  Beat Von Arx

IPC: F01D5/08 ,  F01D5/18

CPC classification number: F01D5/187 ,  B22C9/04 ,  B22C9/108 ,  F05D2230/21 ,  Y10T29/49243 ,  Y10T29/49245

Abstract: A method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a single cooling air channel running in the blade longitudinal direction from the blade root to the blade tip. The method includes, during the casting of the blade, the blade material being fed exclusively from the blade root into the mold provided therefor, and the cooling air channel is formed during the casting of the blade by using a single core body, which is provided, at the blade tip, with a local casting cross section increasing element.

Abstract translation: 提供了一种用于通过铸造生产用于燃气轮机的叶片的方法。 叶片包括沿叶片纵向方向延伸的细长翼型件，在下端处并入叶片根部，在叶片尖端处具有护罩段，并且由叶片纵向方向上从叶片延伸的单个冷却空气通道渗出 根到叶片尖端。 该方法包括在刀片铸造过程中，将刀片材料从叶片根部单独供给到为其提供的模具中，并且通过使用单个芯体在铸造刀片期间形成冷却空气通道，所述单个芯体 ，在叶片尖端处，具有局部铸造截面增加元件。

公开(公告)号：US08147190B2

公开(公告)日：2012-04-03

申请号：US12884875

申请日：2010-09-17

Applicant: Igor Tsypkaykin ,  Beat Von Arx ,  Christoph Nagler

Inventor： Igor Tsypkaykin ,  Beat Von Arx ,  Christoph Nagler

IPC: F04D29/54

CPC classification number: F01D9/042 ,  F05D2260/30

Abstract: A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer platform, the inner side of which is exposed to the hot gas which flows through the gas turbine, and on which provision is made for a hook-like fastening element, projecting outwards in the region of the trailing edge, for fastening the stator vane on a casing of the gas turbine, which fastening element, on its side facing the trailing edge, has a locating slot above the trailing edge for the fixing of a heat shield which adjoins the outer platform of the stator vane in the flow direction of the hot gas. Provision is made on the outer platform of the stator vane between the locating slot and the trailing edge of a structure for reducing the thermal and mechanical stresses in the region of the transition between trailing edge and outer platform.

Abstract translation: 一种用于燃气轮机的定子叶片包括沿着叶片的纵向方向延伸并由前缘和后缘限定的叶片翼片，以及外平台，其内侧暴露于热气体 其流过燃气轮机，并且在其上设置用于钩状紧固元件，其在后缘的区域中向外突出，用于将定子叶片紧固在燃气轮机的外壳上，该紧固元件在其上 面向后缘的侧面具有位于后缘上方的定位槽，用于固定与热气体的流动方向相邻的定子叶片的外平台的隔热罩。 在定子叶片的外平台上在定位槽和结构的后缘之间进行设置，以减少后缘和外平台之间的过渡区域内的热应力和机械应力。

公开(公告)号：US20100166563A1

公开(公告)日：2010-07-01

申请号：US12701852

申请日：2010-02-08

Applicant: Helmar WUNDERLE ,  Stefan SCHLECHTRIEM ,  Peter GRAF ,  Silvio GLASER ,  Beat VON ARX

Inventor： Helmar WUNDERLE ,  Stefan SCHLECHTRIEM ,  Peter GRAF ,  Silvio GLASER ,  Beat VON ARX

IPC: F01D5/30 ,  B23P15/04

CPC classification number: F01D5/3007 ,  F01D11/005 ,  F05D2240/55 ,  F05D2250/13 ,  F05D2250/182 ,  Y10T29/49316

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20100124493A1

公开(公告)日：2010-05-20

申请号：US12617310

申请日：2009-11-12

Applicant: Brian Kenneth WARDLE ,  Thomas Peter SOMMER ,  Beat Von ARX ,  Andre Saxer

Inventor： Brian Kenneth WARDLE ,  Thomas Peter SOMMER ,  Beat Von ARX ,  Andre Saxer

IPC: F01D9/02 ,  B22D23/00 ,  B22D25/00

CPC classification number: F01D9/041 ,  B22C9/043 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/40 ,  Y02T50/671 ,  Y02T50/673

Abstract: Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.

Abstract translation: 提供了一种工业燃气轮机多叶片段，其可以使用蜡模式法一体铸造。 多叶片段包括一个平台; 从平台径向延伸的至少三个翼型件，具有组合的翼型体积，弦长和翼型件厚度; 以及具有护罩体积的护罩，其设置在径向远离平台的所述翼型件的端部上。 护罩体积与组合的翼型体积的比值定义第一比例，而多叶片段具有大于或等于1.4:1的第一比例。 该比率使得在浇铸之前优先凝固翼片前的翼型件。

公开(公告)号：US07520724B2

公开(公告)日：2009-04-21

申请号：US11483091

申请日：2006-07-10

Applicant: Shailandra Naik ,  Sacha Parneix ,  Ulrich Rathmann ,  Helene Saxer-Felici ,  Stefan Schlechtriem ,  Beat Von Arx

Inventor： Shailandra Naik ,  Sacha Parneix ,  Ulrich Rathmann ,  Helene Saxer-Felici ,  Stefan Schlechtriem ,  Beat Von Arx

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/081 ,  F05D2250/50 ,  F05D2260/205 ,  F05D2260/221

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06340284B1

公开(公告)日：2002-01-22

申请号：US09471410

申请日：1999-12-23

Applicant: Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

Inventor： Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

IPC: F01D518

CPC classification number: F01D5/225 ,  F01D5/187 ,  F05D2240/81

Abstract: In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space. The top side of the shroud band is preferable provided with at least two ribs and, which run in parallel and, in interaction with the opposite casing wall, form a cavity, into which the cooling air discharging from the cooling bores flows.

Abstract translation: 在风冷涡轮机叶片中，在叶片尖端处具有横向于叶片的纵向轴线延伸的护罩带元件，多个冷却孔穿过护罩带元件用于冷却，该冷却 孔在入口侧连接到至少一个冷却空气通道，该冷却空气通道穿过涡轮机叶片到达叶片尖端，并且在出口侧打开到围绕涡轮机叶片的外部空间中，由于以下事实实现了改进和确保的冷却： 所述冷却孔在所述护罩带元件中从内到外延伸至少大致平行于所述叶片的运动方向，并且在每种情况下，在所述护罩带元件的外缘的上游开口朝向所述外部开口的表面凹部 空间。 护罩带的顶侧优选设置有至少两个肋，并且平行延伸并且与相对的壳体壁相互作用形成空腔，冷却孔从冷却孔排出的冷却空气流过。

公开(公告)号：US20110286849A1

公开(公告)日：2011-11-24

申请号：US13091605

申请日：2011-04-21

Applicant: Igor TSYPKAYKIN ,  Ruben Valiente ,  Brian Kenneth Wardle ,  Beat Von Arx ,  Andre Saxer

Inventor： Igor TSYPKAYKIN ,  Ruben Valiente ,  Brian Kenneth Wardle ,  Beat Von Arx ,  Andre Saxer

IPC: F01D5/14

CPC classification number: F01D5/225 ,  F05B2240/33

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110189002A1

公开(公告)日：2011-08-04

申请号：US13012317

申请日：2011-01-24

Applicant: Georgeta-Ileana Panaite ,  Igor Tsypkaykin ,  Beat Von Arx ,  Andre Saxer

Inventor： Georgeta-Ileana Panaite ,  Igor Tsypkaykin ,  Beat Von Arx ,  Andre Saxer

IPC: F01D9/04

CPC classification number: F01D9/042 ,  F01D25/246 ,  F05D2230/64 ,  F05D2240/80

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06547525B2

公开(公告)日：2003-04-15

申请号：US09984204

申请日：2001-10-29

Applicant: Hartmut Haehnle ,  Ibrahim El-Nashar ,  Rudolf Kellerer ,  Beat Von Arx

Inventor： Hartmut Haehnle ,  Ibrahim El-Nashar ,  Rudolf Kellerer ,  Beat Von Arx

IPC: F01D508

CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/24 ,  Y10T29/49341

Abstract: 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.

公开(公告)号：US06516865B1

公开(公告)日：2003-02-11

申请号：US09650407

申请日：2000-08-29

Applicant: Alexander Beeck ,  Erhard Kreis ,  Ibrahim El-Nashar ,  Beat Von Arx

Inventor： Alexander Beeck ,  Erhard Kreis ,  Ibrahim El-Nashar ,  Beat Von Arx

IPC: B22D2704

CPC classification number: B22C21/14 ,  B22D31/002 ,  Y10S415/915 ,  Y10T29/49742 ,  Y10T29/49744

Abstract: 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.

Abstract translation: 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。