公开(公告)号：US06446710B2

公开(公告)日：2002-09-10

申请号：US09726424

申请日：2000-12-01

申请人： Alexander Beeck ,  Bernhard Bonhoff ,  Sacha Parneix ,  Bernhard Weigand

发明人： Alexander Beeck ,  Bernhard Bonhoff ,  Sacha Parneix ,  Bernhard Weigand

IPC分类号： F28F1312

CPC分类号： F01D5/187 ,  F05D2260/22141 ,  F23R2900/03045 ,  F28F1/40 ,  F28F3/02 ,  F28F13/12 ,  Y10T137/2093

摘要： An arrangement for cooling a flow-passage wall surrounding a flow passage is described, having at least one rib element which induces flow vortices in a flow medium passing through the flow passage, is attached to that side of the flow-passage wall which faces the flow passage, and the shape and size of which are selected in accordance with a certain heat transfer coefficient and a certain pressure loss caused in the flow medium due to the latter flowing over the rib element. The invention is characterized in that the rib element, while largely retaining its original shape and/or size, has contours enlarging its surface facing the flow passage.

摘要翻译： 描述了用于冷却围绕流动通道的流动通道壁的布置，其具有至少一个在通过流动通道的流动介质中引起流动涡流的肋元件，其连接到流动通道壁的面向 流动通道，其形状和尺寸根据一定的传热系数和由于流体介质流过肋元件而在流动介质中引起的一定的压力损失来选择。本发明的特征在于， 虽然在很大程度上保持其原始形状和/或尺寸，但是其轮廓扩大了其面向流动通道的表面。

公开(公告)号：US06343474B1

公开(公告)日：2002-02-05

申请号：US09401309

申请日：1999-09-23

申请人： Alexander Beeck ,  Beat Von Arx ,  Konrad Vogeler ,  Bernhard Weigand

发明人： Alexander Beeck ,  Beat Von Arx ,  Konrad Vogeler ,  Bernhard Weigand

IPC分类号： F02C100

CPC分类号： F01D5/187 ,  F05D2260/2212 ,  F05D2260/22141

摘要： A cooling passage of a component subjected to high thermal loading, which is formed as a cavity (2, 20, 30), running in a longitudinal direction (L) and curved orthogonally to the longitudinal direction (L), between a first wall (5) and a second wall (6), which in each case are connected to one another in a laterally adjacent manner, which has ribs (7, 17, 27), which are arranged on the first wall (5) and the second wall (6) such that they alternate in a longitudinal direction (L) and are staggered relative one another and, at least in sections, assume a non-orthogonal angle relative to a projected center axis (10′), and through which a cooling fluid (K) can flow in a longitudinal direction (L), in which case, when the profile of the cavity (2, 20, 30) is curved orthogonally to the longitudinal direction (L), the ribs (7, 17, 27) are formed in such a way that, in each case locally with regard to the adjacent rib of the opposite wall, they maintain a distance (a) which is half a respective local rib spacing (p). It is thereby possible to even out the heat transfer at a curved passage profile.

摘要翻译： 形成为沿纵向方向（L）延伸并且与纵向方向（L）垂直弯曲的空腔（2,20,30）的经受高热负荷的部件的冷却通道在第一壁（ 5）和第二壁（6），其在每种情况下以横向相邻的方式彼此连接，其具有布置在第一壁（5）上的肋（7,17,27）和第二壁 （6），使得它们在纵向方向（L）交替并相对于彼此交错，并且至少在部分中相对于突出的中心轴线（10'）呈非正交角，通过该冷却流体 （K）可以在纵向方向（L）上流动，在这种情况下，当空腔（2,20,30）的轮廓与纵向方向（L）正交时，肋（7,17,27） 形成为使得在每种情况下局部地相对于相对的壁的相邻肋，它们保持距离（a）为相对的一半 局部肋间距（p）。 从而可以在弯曲通道轮廓下均匀地传热。

公开(公告)号：US06312218B1

公开(公告)日：2001-11-06

申请号：US09414968

申请日：1999-10-12

申请人： Alexander Beeck ,  Mohamed Nazmy ,  Bernhard Weigand

发明人： Alexander Beeck ,  Mohamed Nazmy ,  Bernhard Weigand

IPC分类号： F01D1100

CPC分类号： F01D11/006 ,  F01D11/005

摘要： Described is a sealing arrangement for reducing leakage flows inside a rotary fluid-flow machine, preferably an axial turbomachine, having moving and guide blades, which are in each case arranged in at least one moving- or guide-blade row respectively and have blade roots, via which the individual moving and guide blades are connected to fastening contours. A sealing element having felt-like material is provided between at least two adjacent blade roots within a guide- or moving-blade row or between guide and/or moving blades and adjacent components of the fluid-flow machine.

摘要翻译： 描述了一种用于减少旋转流体流动机器（优选轴向涡轮机）内的泄漏流的密封装置，其具有移动和导向叶片，每个移动和导向叶片分别布置在至少一个移动或导向叶片排中并具有叶片根部 单独的移动和导向叶片通过其连接到紧固轮廓。 具有毛毡状材料的密封元件设置在导向或移动叶片排中的至少两个相邻叶片根之间或在流体流动机器的引导和/或移动叶片和相邻部件之间。

公开(公告)号：US06644920B2

公开(公告)日：2003-11-11

申请号：US09991970

申请日：2001-11-26

申请人： Alexander Beeck ,  Bernhard Weigand

发明人： Alexander Beeck ,  Bernhard Weigand

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  B23H9/10 ,  B23H9/14 ,  B23H9/16 ,  F01D5/186 ,  F05D2230/12 ,  F05D2240/81 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2250/71 ,  Y10T29/49341

摘要： A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central rotational axis of the helix and axially along the central rotational axis. A turbine blade for a gas turbine component is provided with at least one helical cooling channel.

摘要翻译： 在涡轮叶片等燃气轮机部件中形成弯曲的冷却通道的方法使用螺旋形式的电极。 电极被驱动以围绕螺旋的中心旋转轴线旋转并沿着中心旋转轴线轴向旋转。 用于燃气涡轮机部件的涡轮机叶片设置有至少一个螺旋形冷却通道。

公开(公告)号：US06422811B1

公开(公告)日：2002-07-23

申请号：US09593162

申请日：2000-06-14

申请人： Alexander Beeck ,  Bernhard Weigand

发明人： Alexander Beeck ,  Bernhard Weigand

IPC分类号： F04D2938

CPC分类号： F01D5/188 ,  F02C7/18 ,  F05D2260/2322

摘要： A cooling arrangement for blades of a gas turbine or the like, in each case the blades being built up from a suction-side wall and a pressure-side wall which are connected, to form a cavity, via a leading edge, a trailing edge, a blade tip and a blade root, and a flow path, through which a cooling medium, in particular steam, is capable of flowing, being integrated in the cavity, and in which the flow paths in each case of two or more adjacent blades are connected to one another in such a way that a continuous cooling duct sealed off relative to the hot-gas stream is formed. It thus becomes possible to increase cooling efficiency by better utilization of the cooling medium and at the same time to reduce the outlay in terms of construction.

摘要翻译： 一种用于燃气轮机等的叶片的冷却装置，在每种情况下，叶片由吸入侧壁和压力侧壁构成，所述吸入侧壁和压力侧壁经由前缘连接以形成空腔，后缘 ，叶片尖端和叶片根部，以及流动路径，冷却介质，特别是蒸汽能够流动通过该流动路径集成在空腔中，并且每个情况下的两个或更多个相邻叶片的流动路径 彼此连接，从而形成相对于热气流密封的连续冷却管道。 因此，可以通过更好地利用冷却介质来提高冷却效率，同时可以减少施工方面的费用。

公开(公告)号：US06340284B1

公开(公告)日：2002-01-22

申请号：US09471410

申请日：1999-12-23

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

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

IPC分类号： F01D518

CPC分类号： F01D5/225 ,  F01D5/187 ,  F05D2240/81

摘要： 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.

摘要翻译： 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：US06276692B1

公开(公告)日：2001-08-21

申请号：US09349963

申请日：1999-07-09

申请人： Alexander Beeck ,  Wilhelm Endres ,  Konrad Vogeler ,  Bernhard Weigand

发明人： Alexander Beeck ,  Wilhelm Endres ,  Konrad Vogeler ,  Bernhard Weigand

IPC分类号： F01D1102

CPC分类号： F16J15/40 ,  F01D11/001 ,  F01D11/04

摘要： The arrangements according to the invention and the methods according to the invention serve to seal a gap 20 against a primary fluid 10 by means of a secondary fluid 11 in a fluid-dynamic and non-contact manner, which primary fluid 10 flows over the gap 20. The secondary fluid 11 forms a preferably rotating vortex flow 13 in the gap in at least one or more sections along the gap. The flow of the secondary fluid 11 is preferably guided in a chamber 26, which is arranged in the gap 20. The chamber 26 is designed as a rotary chamber along the entire gap 20 or also as a local chamber 226 extending only locally along the gap. The secondary fluid 11 may be supplied via supply conduits 40, in which the gap 120 itself may be utilized for supplying secondary fluid 115 to the chamber 126. As further elements for the guidance of the vortex flow, guiding lips 50, undercuts of the chamber contour 351, and guiding elements 160 may be arranged in the gap. Furthermore, a mechanical seal 370 arranged in the gap on that side of the chamber which is remote from the primary flow may additionally seal the gap 320 mechanically. A typical embodiment of the invention is shown in FIG. 1. A second arrangement according to the invention relates to a slalom chamber 690, which is arranged in S-shaped undulations along the gap 620.

摘要翻译： 根据本发明的装置和根据本发明的方法用于通过流体动力学和非接触方式的第二流体11密封间隙20抵靠初级流体10，初级流体10流过间隙 次级流体11沿着间隙在至少一个或多个部分中的间隙中形成优选旋转的涡流13。 次级流体11的流动优选地在布置在间隙20中的腔室26中引导。腔室26被设计为沿着整个间隙20的旋转腔室，或者也被设计为局部腔室226，局部腔室226仅沿着间隙 。 次级流体11可以经由供应管道40供应，其中间隙120本身可用于将二次流体115供应到室126.作为用于引导涡流的另外的元件，引导唇缘50，腔室的底切 轮廓351和引导元件160可以布置在间隙中。 此外，布置在远离主流的室的该侧上的间隙中的机械密封件370可另外机械地密封间隙320。 图1中示出了本发明的典型实施例。 根据本发明的第二种装置涉及一种沿着间隙620布置成S形波纹的回旋室690。

公开(公告)号：US6068445A

公开(公告)日：2000-05-30

申请号：US111706

申请日：1998-07-08

申请人： Alexander Beeck ,  Bruce Johnson ,  Bernhard Weigand ,  Pey-Shey Wu

发明人： Alexander Beeck ,  Bruce Johnson ,  Bernhard Weigand ,  Pey-Shey Wu

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2260/22141

摘要： In a cooling system for the leading-edge region of a hollow gas-turbine blade, a duct (3), through which flow occurs longitudinally, extends from the blade root up to the blade tip and is defined in the region of the blade body (4) by the inner walls of the leading edge (5), the suction side (6) and the pressure side (7) and by a web (8). The inner walls of the suction side and the pressure side are provided with a plurality of ribs (9), which run slantwise and at least approximately in parallel. The suction-side ribs and the pressure-side ribs are offset from one another over the blade height. The ribs (9) run radially inward from the web (8) in the direction of the leading edge (5), merge into the radial in the region of the leading edge and are led around the leading edge. The deviation of the ribs (9) from the slant into the radial is effected with the smallest possible radius. The ratio of the height (h) of the ribs (9) to the local height (H) of the duct (3) is constant over the longitudinal extent of the ribs.

摘要翻译： 在用于中空燃气涡轮机叶片的前缘区域的冷却系统中，纵向发生流动的管道（3）从叶片根部向上延伸到叶片尖端并限定在叶片体的区域 （5）的内壁，吸力侧（6）和压力侧（7）以及腹板（8）之间。 吸入侧和压力侧的内壁设置有多个倾斜且至少大致平行的肋（9）。 吸力侧肋和压力侧肋在刀片高度上彼此偏移。 沿着前缘（5）的方向从腹板（8）径向向内延伸的肋（9）在前缘的区域中合并成径向，并且围绕前缘引导。 肋（9）从斜面到径向的偏差以尽可能小的半径进行。 肋（9）的高度（h）与管道（3）的局部高度（H）的比率在肋的纵向范围内是恒定的。

公开(公告)号：US06575698B2

公开(公告)日：2003-06-10

申请号：US09897477

申请日：2001-07-03

申请人： Alexander Beeck ,  Ulrich Rathmann ,  Hans E. Wettstein

发明人： Alexander Beeck ,  Ulrich Rathmann ,  Hans E. Wettstein

IPC分类号： F01D1108

CPC分类号： F01D11/127 ,  F05D2250/283

摘要： A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.

摘要翻译： 蜂窝结构设置在燃气轮机的定子上并与燃气轮机的动叶片相对设置。 蜂窝结构由金属板构成，从而获得双层厚度的纤维网，并且在幅材之间获得单一厚度的连接。 定子的圆周方向与双层厚度的腹板之间的角度α为5°至175°。 这用于避免不期望的努力，例如在燃气轮机的动叶片的蜂窝结构处的摩擦期间过热。

公开(公告)号：US06534975B2

公开(公告)日：2003-03-18

申请号：US09754188

申请日：2001-01-05

申请人： Alexander Beeck ,  Andreas Boegli ,  John Fernihough ,  Klaus Schneider

发明人： Alexander Beeck ,  Andreas Boegli ,  John Fernihough ,  Klaus Schneider

IPC分类号： G01B706

CPC分类号： G01B21/085 ,  C23C4/12 ,  F01D5/288 ,  G01B1/00 ,  G01B7/105 ,  G01B17/025

摘要： A nondestructive method for determining the thickness of a metallic protective layer determined by detection of a different type of intervening layer which is situated between the metallic protective layer and the metallic base material, by ultrasound, eddy-current or (pulsed) thermography. The intervening layer may comprise a nonmetallic layer of oxides or carbides, a metallic layer of pure nickel or a layer with depleted Al and Ti content in that region of the base material which is close to the surface. This method can be used for turbine blades in order to determine the layer thickness, for example during the test phase of coating, and to avoid the known destruction of the turbine blade, which is labor- and cost-intensive.

摘要翻译： 通过超声，涡流或（脉冲）热成像法检测位于金属保护层和金属基材之间的不同类型的中间层确定金属保护层的厚度的非破坏性方法。 中间层可以包括氧化物或碳化物的非金属层，纯镍的金属层或在靠近表面的基材的区域中具有贫化的Al和Ti含量的层。 为了确定层厚度，例如在涂层的测试阶段，这种方法可以用于涡轮叶片，并且避免已经破坏涡轮叶片，这是劳力和成本密集型的​​。