公开(公告)号：US06374898B1

公开(公告)日：2002-04-23

申请号：US09268722

申请日：1999-03-17

申请人： Konrad Vogeler ,  Bernhard Weigand ,  Hans Wettstein

发明人： Konrad Vogeler ,  Bernhard Weigand ,  Hans Wettstein

IPC分类号： B22C910

CPC分类号： B22C9/22 ,  B22C9/18

摘要： A process for producing a casting core which is used for forming within a casting a cavity intended for cooling purposes, through which a cooling medium can be conducted, the casting core having surface regions in which there is incorporated in a specifically selective manner a surface roughness which transfers itself during the casting operation to surface regions enclosing the cavity and leads to an increase in the heat transfer between the cooling medium and the casting.

摘要翻译： 一种铸造芯的制造方法，其用于在铸件内形成用于冷却目的的空腔，通过该铸造芯可以进行冷却介质，铸造芯具有以特定选择性方式结合的表面区域的表面粗糙度 其在铸造操作期间将其自身转移到包围空腔的表面区域，并导致冷却介质和铸件之间的热传递增加。

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：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：US06224328B1

公开(公告)日：2001-05-01

申请号：US09371904

申请日：1999-08-11

申请人： Bernhard Weigand ,  Conor Fitzsimons ,  Wolfgang Kappis ,  Hans Wettstein

发明人： Bernhard Weigand ,  Conor Fitzsimons ,  Wolfgang Kappis ,  Hans Wettstein

IPC分类号： F01D514

CPC分类号： F01D11/16 ,  F01D5/08 ,  F01D5/187 ,  F01D11/10 ,  F05D2260/201

摘要： Turbomachine, in particular a compressor of a gas turbine, having rotor blades (11) and guide vanes (12), in which individual or all guide vanes (12) are configured as cooled vanes. The cooled vanes (12) have air guidance ducts (13) which emerge into outlet openings (14) in the region of the vane tips (15). Cooling air (K) is ejected through the outlet openings (14) and impinges at high velocity onto a rotor shaft (18). The cooling effect which can be achieved by this means is optimal and, in addition, leads to a raising of the compressor efficiency and the surge line.

摘要翻译： 涡轮机械，特别是具有转子叶片（11）和导向叶片（12）的燃气涡轮机的压缩机，其中单个或全部导向叶片（12）被构造为冷却叶片。 冷却的叶片（12）具有在叶片尖端（15）的区域中出现到出口（14）中的空气引导管道（13）。 冷却空气（K）通过出口（14）排出并以高速冲击到转子轴（18）上。 通过这种方式可以实现的冷却效果是最佳的，并且另外导致压缩机效率和喘振线的提高。

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：US06305903B1

公开(公告)日：2001-10-23

申请号：US09379465

申请日：1999-08-24

申请人： Klaus Semmler ,  Bernhard Weigand

发明人： Klaus Semmler ,  Bernhard Weigand

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  F05D2260/221

摘要： A cooled vane for a gas turbine or similar device including a vane blade constructed of a suction side wall and a pressure side wall that are connected via a leading edge and a trailing edge with each other, which has an essentially radially extending cavity through which a cooling medium is capable of flowing. The vane blade has multiple cooling channels that, starting from the cavity, extend through a vane section adjoining the trailing edge and formed by sections of the suction side wall and the pressure side wall, and end at the trailing edge. A first row of cooling channels is associated with the suction side (SS) of the vane blade, and a second row of cooling channels is associated with the pressure side (DS) of the vane blade. The cooled vane has improved cooling efficiency and can be produced entirely with a casting process while complying with basic geometric conditions.

摘要翻译： 一种用于燃气轮机或类似装置的冷却叶片，包括由吸入侧壁和压力侧壁构成的叶片叶片，该叶片叶片经由前缘和后缘彼此连接，所述侧壁具有基本上径向延伸的空腔， 冷却介质能够流动。 叶片叶片具有多个冷却通道，其从腔体开始延伸通过与后缘相邻的叶片部分并且由吸力侧壁和压力侧壁的部分形成并且在后缘处结束。 第一排冷却通道与叶片的吸入侧（SS）相关联，第二排冷却通道与叶片的压力侧（DS）相关联。 冷却的叶片具有提高的冷却效率，并且可以在符合基本几何条件的情况下通过铸造工艺完全制造。

公开(公告)号：US07137777B2

公开(公告)日：2006-11-21

申请号：US10882335

申请日：2004-07-02

申请人： Reinhard Fried ,  Bernhard Weigand

发明人： Reinhard Fried ,  Bernhard Weigand

IPC分类号： F01D5/12

CPC分类号： F01D5/082 ,  F01D11/001 ,  F05D2260/607

摘要： A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90°.

摘要翻译： 一种装置将外来颗粒与供给到涡轮转子叶片的冷却空气分离。 冷却空气通过固定喷嘴单元被直接地或间接地供给到涡轮机定子的壁部分与旋转轮盘之间的环形空间，作为在圆周方向上的冷却空气流。 环形空间与布置在盘中的管道连通，用于将冷却空气供给到叶片中。 在环形空间内设置转向单元，或者在一侧限定环形空间，从而在进入导管之前从喷嘴单元排出的冷却空气在一侧被转向，异物将离心地投入到径向外侧 环形空间的一部分并与阻挡空气部分分离。 分流器单元具有流体撞击的表面区域，使得其可以径向向外转过大于90°的角度。

公开(公告)号：US06464460B2

公开(公告)日：2002-10-15

申请号：US09725722

申请日：2000-11-30

申请人： Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand ,  Hartmut Haehnle ,  Rudolf Kellerer

发明人： Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand ,  Hartmut Haehnle ,  Rudolf Kellerer

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2240/81 ,  F05D2250/141

摘要： In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).

摘要翻译： 在风叶涡轮叶片（10）中，在叶片尖端处具有护罩带元件（11），所述护罩带元件（11）横向于叶片纵向轴线延伸，中空空间（16,16'，17 ，17'）设置在所述护罩带元件（11）的内部，所述中空空间（16,16'，17,17'）在入口侧连接到至少一个冷却空气通道（ 18）通过涡轮机叶片（10）到叶片尖端并且在出口侧打开到围绕涡轮机叶片（10）的外部空间中，中空空间（16,16'，17,17'）和护罩 - 带元件（11）的形状和尺寸彼此匹配，以便减少护罩带元件（11）的重量。