公开(公告)号：US08006381B2

公开(公告)日：2011-08-30

申请号：US12633541

申请日：2009-12-08

申请人： Hartmut Haehnle ,  Ingo Schwarz ,  Christoph Nagler

发明人： Hartmut Haehnle ,  Ingo Schwarz ,  Christoph Nagler

IPC分类号： B23P6/00

CPC分类号： F01D5/005 ,  F01D5/225 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49716

摘要： A method of modifying an existing casting mold for a turbine moving blade having a shroud band segment with an initial coupling geometry for coupling with a further shroud band segment, the coupling geometry having an initial coupling angle of the shroud band segment relative to a circumferential direction of the turbine, includes calculating a modified coupling geometry for the shroud band segment, the modified coupling geometry including a modified coupling angle of the shroud band segment relative to the circumferential direction. The method further includes creating at least one of a removal zone and an application zone, wherein the creating of the removal zone includes removing a first amount of casting mold material from the removal zone and wherein the creating of the application zone includes applying a second amount of an additional casting mold material to the application zone, wherein the removing and the applying steps result in the casting mold having the modified coupling angle.

摘要翻译： 一种用于涡轮机动叶片的现有铸模的修改方法，所述铸造模具具有具有初始耦合几何形状的护罩带段，用于与另一护罩带段联接，所述耦合几何形状具有所述护罩带段相对于圆周方向的初始耦合角度 所述涡轮机包括计算用于所述护罩带段的改进的联接几何形状，所述改进的联接几何形状包括所述护罩带段相对于所述圆周方向的改进的联接角度。 所述方法还包括产生去除区域和施用区域中的至少一个，其中所述去除区域的产生包括从所述去除区域移除第一量的铸模材料，并且其中所述施加区域的产生包括施加第二量 的额外的铸模材料施加到施加区域，其中移除和施加步骤导致具有改变的联接角度的铸模。

公开(公告)号：US06726391B1

公开(公告)日：2004-04-27

申请号：US09638002

申请日：2000-08-14

申请人： Erhard Kreis ,  Christoph Nagler ,  Ulrich Rathmann

发明人： Erhard Kreis ,  Christoph Nagler ,  Ulrich Rathmann

IPC分类号： F03B1100

CPC分类号： F16B1/00 ,  F01D25/246 ,  F05D2230/642 ,  Y10T403/21 ,  Y10T403/70

摘要： A device for fastening and fixing components to a cylindrical wall. The cylindrical wall may be both the convex-cylindrical outer contour of a cylinder and the concave-cylindrical inner contour of a hollow cylinder, in which the component is fixed in the radial, axial and circumferential directions. The fastening and fixing is effected by shaped elements which are attached to the component and by a counterpart to each shaped element on the wall. In each case a shaped element and a counterpart interlock, such that the component has at least three shaped elements, of which at least one shaped element has a defined accuracy of fit with its associated counterpart in the radial direction and has clearance in the axial and circumferential directions. At least one shaped element has a defined accuracy of fit with its associated counterpart in the axial direction and has clearance in the radial and circumferential directions. Furthermore, at least one shaped element has a defined accuracy of fit with its associated counterpart in the circumferential direction and has clearance in the radial and axial directions.

摘要翻译： 用于将部件紧固并固定到圆柱形壁的装置。 圆柱形壁可以是圆柱体的凸圆柱形外轮廓和中空圆柱体的凹圆柱形内轮廓，其中部件沿径向，轴向和圆周方向固定。 紧固和固定由成形元件实现，该元件连接到部件上，并由对应物连接到壁上的每个成形元件。 在每种情况下，成形元件和对应物互锁件，使得该部件具有至少三个成形元件，其中至少一个成形元件具有与其相关联的对应物在径向方向上的限定的配合精度，并且在轴向和 圆周方向。 至少一个成形元件具有与其相关联的对应物在轴向上的限定的配合精度，并且在径向和圆周方向上具有间隙。 此外，至少一个成形元件在圆周方向上具有与其相关联的对应物的限定的配合精度，并且在径向和轴向方向上具有间隙。

公开(公告)号：US08147190B2

公开(公告)日：2012-04-03

申请号：US12884875

申请日：2010-09-17

申请人： Igor Tsypkaykin ,  Beat Von Arx ,  Christoph Nagler

发明人： Igor Tsypkaykin ,  Beat Von Arx ,  Christoph Nagler

IPC分类号： F04D29/54

CPC分类号： F01D9/042 ,  F05D2260/30

摘要： 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.

摘要翻译： 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：US20110014054A1

公开(公告)日：2011-01-20

申请号：US12827696

申请日：2010-06-30

申请人： Christoph NAGLER ,  Jose Anguisola Mc Feat ,  Sergei Riazantsev ,  Marcel Koenig ,  Erich Kreiselmaier

发明人： Christoph NAGLER ,  Jose Anguisola Mc Feat ,  Sergei Riazantsev ,  Marcel Koenig ,  Erich Kreiselmaier

IPC分类号： F01D5/30 ,  B23P6/00

CPC分类号： F01D9/02 ,  F01D5/005 ,  F05D2240/80

摘要： The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.

摘要翻译： 燃气轮机的引导叶片包括具有可连接到导向叶片承载件或燃气轮机壳体的外部平台的叶片，并且在相对端具有承载盖板的内部平台。 内平台具有连接盖板的燕尾形外壳。 更换盖板的方法在于通过沿着燕尾形外壳的轮廓切割将盖板与内平台分开，然后使盖板从燕尾壳体滑出，从而将新的或翻新的盖板插入 燕尾屋

公开(公告)号：US06640597B2

公开(公告)日：2003-11-04

申请号：US10003231

申请日：2001-12-06

申请人： Alexander Beeck ,  Christoph Nagler ,  Mark Richter

发明人： Alexander Beeck ,  Christoph Nagler ,  Mark Richter

IPC分类号： B21D102

CPC分类号： F01D5/186 ,  B23P9/00 ,  B23P2700/06 ,  F05D2230/10 ,  F05D2230/90 ,  F05D2250/25 ,  Y10T29/47

摘要： A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.

公开(公告)号：US06481966B2

公开(公告)日：2002-11-19

申请号：US09739282

申请日：2000-12-19

申请人： Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

发明人： Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

IPC分类号： F01D518

CPC分类号： B22D11/0405 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304

摘要： In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).

摘要翻译： 在热空气流（23）流过的燃气涡轮引导元件（30）中，并且至少在其中气流（23）与引导元件（30）分离的后缘区域（21）中， 至少两个壁（10,11），其基本上平行布置并且通过肋（16,17,20）彼此连接，以形成内部冷却通道（18,19,25,26,27） 并且在流过冷却通道（18,19,25,26,27）的冷却介质（28,29）在内部冷却，冷却介质从后缘（21）处的引导元件（30）排出 ）基本上平行于壁（10,11），并且在其制造方法中，由于至少一些肋布置为扼流肋（24），实现了更容易的再加工和对外来颗粒的较小的敏感性 ），以便基本上与后缘（21）齐平地终止。

公开(公告)号：US06322320B1

公开(公告)日：2001-11-27

申请号：US09450728

申请日：1999-11-30

申请人： Christof Pfeiffer ,  Ulrich Wellenkamp ,  Christoph Nagler

发明人： Christof Pfeiffer ,  Ulrich Wellenkamp ,  Christoph Nagler

IPC分类号： F04D3100

CPC分类号： F01D11/08 ,  F01D11/24 ,  F01D25/246 ,  F05D2260/201

摘要： A coolable casing of a gas turbine or the like, with a plurality of arcuate casing segments (10) which are arranged so as to be contiguous with one another in a circumferential direction, to form an essentially closed casing ring surrounding a rotor (110), in particular of a high-pressure turbine, at least one annular casing cooling chamber (15) which is formed in the radial direction between the casing segments (10) and arcuate guide segments (30) provided with a multiplicity of passage orifices (34), at least one air guide chamber (25) which is formed in the radial direction between the guide segments (30) and at least one carrier segment (20), and at least one air supply duct (26) which is made on the carrier segment (20) and opens into the air guide chamber (25), the guide segments (30) being mounted loosely with radial play. This ensures stress-free reception, even in the case of intensive operations having high temperature gradients.

摘要翻译： 一种燃气轮机等的可冷却壳体，具有多个弓形壳体段（10），其沿圆周方向彼此邻接设置，以形成围绕转子（110）的基本封闭的壳体环， 特别是高压涡轮机的至少一个环形壳体冷却室（15），其沿径向形成在壳体段（10）和具有多个通道孔（34）的弓形引导段（30）之间， ），至少一个空气引导室（25），其在径向方向上形成在引导段（30）和至少一个载体段（20）之间，以及至少一个空气供应管道（26） 载体段（20）并且通向导风室（25），引导段（30）以径向游隙松散地安装。 这确保了无压力的接收，即使在具有高温度梯度的密集操作的情况下也是如此。

公开(公告)号：US06302642B1

公开(公告)日：2001-10-16

申请号：US09551565

申请日：2000-04-18

申请人： Christoph Nagler ,  Christof Pfeiffer ,  Ulrich Wellenkamp

发明人： Christoph Nagler ,  Christof Pfeiffer ,  Ulrich Wellenkamp

IPC分类号： F04D3100

CPC分类号： F01D25/12 ,  F01D11/24

摘要： A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and consists of a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms of which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of heat-shield segments and the adjacent elements which define the hot-gas duct on the outside.

摘要翻译： 用于燃气轮机的隔热罩，其隔热罩以环形方式围绕在燃气轮机的一级的燃气轮机的热气管道中旋转的活动叶片，并且由多个隔热板段组成， 在圆周方向上一个接一个地布置，弯曲成圆形的部分的形状并且从外部被冷却，并且被设计为相应的弯曲轨道的纵向侧面在圆周方向上延伸，并且在每种情况下都是 一对臂在轴向方向上突出并平行并且彼此间隔一段距离，隔热片段在形成可容纳冷却空气的空腔的同时被固定到环形载体的内部 ，其同心地围绕隔热罩，使得在每种情况下，在隔热片段的纵向侧面和限定外部的热气管道的相邻元件之间形成径向间隙 de。

公开(公告)号：US08920110B2

公开(公告)日：2014-12-30

申请号：US12783046

申请日：2010-05-19

申请人： Jose Anguisola McFeat ,  Erich Kreiselmaier ,  Christoph Nagler ,  Sergei Riazantsev

发明人： Jose Anguisola McFeat ,  Erich Kreiselmaier ,  Christoph Nagler ,  Sergei Riazantsev

IPC分类号： F01D5/18 ,  F01D9/02

CPC分类号： F01D5/186 ,  F01D5/188 ,  F01D9/02 ,  F05D2240/81 ,  F05D2260/201

摘要： The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.

摘要翻译： 本发明涉及一种中空燃气涡轮机叶片，该中空燃气涡轮机叶片由构造成顺序冷却叶片的端壁及其翼型并且同时为叶片的两个端壁顺序冷却的装置而冷却。 这种布置可以减少冷却空气需求，这可能对涡轮机的效率产生积极的影响。

公开(公告)号：US08142143B2

公开(公告)日：2012-03-27

申请号：US12884851

申请日：2010-09-17

申请人： Erich Kreiselmaier ,  Jose Anguisola McFeat ,  Christoph Nagler ,  Sergei Riazantsev ,  Brian Kenneth Wardle

发明人： Erich Kreiselmaier ,  Jose Anguisola McFeat ,  Christoph Nagler ,  Sergei Riazantsev ,  Brian Kenneth Wardle

IPC分类号： F04D29/54

CPC分类号： F01D25/246 ,  F01D11/005 ,  F01D25/08 ,  F05D2240/10 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2270/114

摘要： A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud.

摘要翻译： 一种用于燃气轮机的定子叶片包括在叶片的纵向方向上延伸并由前缘和后缘限定的叶片翼型件。 定子叶片包括护罩，其内侧暴露于流过燃气轮机的热气体。 用于将定子叶片紧固在燃气涡轮机壳体上的钩状紧固元件在后缘区域中向外突出。 紧固元件具有在后缘上方的定位槽，用于固定热屏蔽件，该隔热罩沿着热气体的流动方向连接到护罩。 在护罩之间设置有用于隔热罩的定位槽和叶片翼型件的后缘之间的空腔，用于减小后缘和护罩之间的过渡区域内的热和机械应力。