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：US06361274B1

公开(公告)日：2002-03-26

申请号：US09632795

申请日：2000-08-04

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： F01D25/246 ,  F01D11/08 ,  F01D11/12

摘要： A fastening device for a heat-protection shield of a gas turbine is provided with a center mounting element which has a defined installation clearance with a mounting slot in the radial direction. In the normal operating state, this mounting element has no function, such that thermal differential expansions in the radial direction between the heat-protection shield and its counterpart are possible without impairment within the limits of this defined clearance. The mounting element does not start to bear against the counterpart until the radial differential expansion exceeds the size s. The deformation of the heat-protection shield toward a component moving in a relative manner is thus limited and excessive grazing of the components against one another is avoided.

摘要翻译： 燃气轮机的保护罩的紧固装置设置有中心安装元件，该中心安装元件在径向方向上与安装槽具有确定的安装间隙。 在正常工作状态下，该安装元件不具有功能，使得在该限定的间隙的限度内，可以在热保护屏蔽件与其对应部件之间的径向方向上的热差扩展而不受损害。 直到径向差分膨胀超过尺寸s，安装元件才能开始抵靠对方。 因此，防护罩朝向相对移动的部件的变形受到限制，并且避免了部件相对于彼此过度的放牧。

公开(公告)号：US07207108B2

公开(公告)日：2007-04-24

申请号：US10713098

申请日：2003-11-17

申请人： Stefan Irmisch ,  Erhard Kreis ,  Christoph Nagler ,  Andre Schwind

发明人： Stefan Irmisch ,  Erhard Kreis ,  Christoph Nagler ,  Andre Schwind

IPC分类号： B21B1/46 ,  B21K25/00

CPC分类号： F01D5/147 ,  B23P15/02 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/80 ,  F05D2250/70 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49336 ,  Y10T29/49989

摘要： In a process for producing a turbine blade or vane, providing a casting mold for casting the turbine blade or vane, the casting mold including a blade or vane platform and a main blade or vane part, and a position of the main blade or vane part relative to the blade or vane platform determining a first angle of incidence; providing additional machining stock to the blade or vane platform at predetermined locations; machining the casting using a process which is specified for the first angle of incidence; rotating the casting around a longitudinal axis for an angle which is equal to the difference between said first angle of incidence and a second angle of incidence, and subjecting said rotated casting to said machining process to remove at least partially the additional machining stock.

摘要翻译： 在制造涡轮叶片或叶片的方法中，提供用于铸造涡轮机叶片或叶片的铸模，所述铸模包括叶片或叶片平台以及主叶片或叶片部分，以及主叶片或叶片部分的位置 相对于叶片或叶片平台确定第一入射角; 在预定位置向叶片或叶片平台提供额外的机加工料; 使用为第一入射角指定的过程来加工铸件; 使所述铸件围绕纵向轴线旋转一角度，所述角度等于所述第一入射角与第二入射角之间的差，并且对所述旋转铸件进行所述机械加工以至少部分去除所述附加机械加工材料。

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：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。

公开(公告)号：US20100077586A1

公开(公告)日：2010-04-01

申请号：US12633541

申请日：2009-12-08

申请人： Hartmut Haehnle ,  Christoph Nagler ,  Ingo Schwarz

发明人： Hartmut Haehnle ,  Christoph Nagler ,  Ingo Schwarz

IPC分类号： B23P17/04

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：US07131814B2

公开(公告)日：2006-11-07

申请号：US10762293

申请日：2004-01-23

申请人： Christoph Nagler ,  André Schwind ,  Ralf Walz

发明人： Christoph Nagler ,  André Schwind ,  Ralf Walz

IPC分类号： F01D11/00

CPC分类号： F01D11/005 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/57 ,  F05D2260/201 ,  F05D2260/607

摘要： A cooling arrangement (17) for supplying a first cavity (9) with a cooling gas, in particular in a gas turbine of a power plant, includes a cooling-gas passage (19) which is formed in a first component (6) and connects the first cavity (9) to a second cavity (10 ). A second component (16 ) bears against a bearing side (15) remote from the second cavity (10 ) and separates the first cavity (9) from a third cavity (12). The second component (16 ) is displaceable within a range of displacement. To improve the cooling effect, an orifice region (20) of the cooling-gas passage (19) is dimensioned and/or positioned in such a way that its orifice cross section (21) projects from the range of displacement to such an extent that it is open at least with a predetermined minimum cross section in any position of the second component (16 ).

摘要翻译： 特别是在发电厂的燃气轮机中供给具有冷却气体的第一空腔（9）的冷却装置（17）包括冷却气体通路（19），其形成在第一部件（6）和 将第一空腔（9）连接到第二腔（10）。 第二部件（16）抵靠远离第二腔（10）的轴承侧（15），并将第一腔（9）与第三腔（12）分离。 第二部件（16）可在位移范围内移位。 为了改善冷却效果，冷却气体通道（19）的孔口区域（20）的尺寸和/或定位方式使得其孔口横截面（21）从位移范围突出到如下程度： 至少在第二部件（16）的任何位置具有预定的最小横截面是开放的。

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：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.